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Sample records for f4c airplane model

  1. MLS: Airplane system modeling

    NASA Technical Reports Server (NTRS)

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

    1981-01-01

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

  2. A computational study of simultaneous cation/anion interactions in model clusters containing all-cis 1,2,3-trifluorocyclopropane (F3C3H3) and all-cis 1,2,3,4-tetrafluorobutane (F4C4H4)

    NASA Astrophysics Data System (ADS)

    McDowell, Sean A. C.

    2016-11-01

    A computational study of two model clusters involving the all-cis 1,2,3-trifluorocyclopropane (F3C3H3) and the all-cis 1,2,3,4-tetrafluorocyclobutane (F4C4H4) molecules was undertaken. These clusters involve the simultaneous attachment of a cation (Li+/Na+) to the "negative" face of F3C3H3/F4C4H4 (via interaction with the Csbnd F bonds) and a model F- anion to the "positive" face of F3C3H3/F4C4H4 (via the adjacent Csbnd H bonds). The relative stabilities of the two model clusters was investigated and extended to the neutral M+sbnd F4C4H4sbnd X- (M = Li, Na, K; X = F, Cl, Br) clusters. The cation-anion electrostatic interaction is the main source of attraction in these highly polar moieties.

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-05

    ...-200 Series Airplanes; Model A330-300 Series Airplanes; Model A340-200 Series Airplanes; and Model A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-25

    ...-200 Series Airplanes; Model A330-300 Series Airplanes; Model A340-200 Series Airplanes; and Model A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... airplanes) or TR150 (for Model A340-200 and -300 series airplanes), both Issue 1.0, both dated December...

  5. 77 FR 2437 - Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane; Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-01-18

    ... Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane... conditions are issued for the Gulfstream Aerospace Corporation (GAC) Model GVI airplane. This airplane...

  6. 75 FR 79952 - Airworthiness Directives; DASSAULT AVIATION Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-21

    ... Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G Airplanes; Model MYSTERE-FALCON 200 Airplanes; Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 Airplanes; Model FALCON 2000 and FALCON 2000EX Airplanes; and Model MYSTERE-FALCON 50 and MYSTERE-FALCON 900...

  7. 75 FR 6157 - Airworthiness Directives; Gulfstream Aerospace LP Model Gulfstream 100 Airplanes, and Model Astra...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-08

    ... Aerospace LP Model Gulfstream 100 Airplanes, and Model Astra SPX and 1125 Westwind Astra Airplanes AGENCY... airplanes; and Model Astra SPX and 1125 Westwind Astra airplanes; certificated in any category; all serial... (AFMs): Model 1125 Astra, 25W-1001-1; Model Astra SPX, SPX-1001-1; and Model G100, G100-1001-1; as...

  8. 78 FR 31835 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Landing Pitchover Condition

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-28

    ..., Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes..., on May 21, 2013. Jeff Duven, Acting Manager, Transport Airplane Directorate, Aircraft...

  9. 77 FR 69747 - Airworthiness Directives; The Boeing Company Model Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-21

    ... Model Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-100 and -200... the affected airplane models should be added to paragraph (j) of this AD for clarification and...

  10. Variable-Structure Control of a Model Glider Airplane

    NASA Technical Reports Server (NTRS)

    Waszak, Martin R.; Anderson, Mark R.

    2008-01-01

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

  11. Modeling of airplane performance from flight-test results and validation with an F-104G airplane

    NASA Technical Reports Server (NTRS)

    Marshall, R. T.; Schweikhard, W. G.

    1973-01-01

    A technique of defining an accurate performance model of an airplane from limited flight-test data and predicted aerodynamic and propulsion system characteristics is developed. With the modeling technique, flight-test data from level accelerations are used to define a 1g performance model for the entire flight envelope of an F-104G airplane. The performance model is defined in terms of the thrust and drag of the airplane and can be varied with changes in ambient temperature or airplane weight. The model predicts the performance of the airplane within 5 percent of the measured flight-test data. The modeling technique could substantially reduce the time required for performance flight testing and produce a clear definition of the thrust and drag characteristics of an airplane.

  12. 76 FR 15872 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-22

    ...-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...-200 and -300 series airplanes and Model A340-200, -300, -500, and -600 series airplanes. That AD... FR 8610, February 15, 2011), for Airbus Model A340-200, -300, -500, and -600 series airplanes,...

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

    NASA Astrophysics Data System (ADS)

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

    2016-06-01

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

  14. 76 FR 31453 - Special Conditions: Gulfstream Model GVI Airplane; Single-Occupant Side-Facing Seats

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ..., Airframe/Cabin Safety Branch, ANM-115, Transport Standards Staff, Transport Airplane Directorate, Aircraft... Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane. The maximum takeoff... Renton, Washington, on May 20, 2011. Ali Bahrami, Manager, Transport Airplane Directorate,...

  15. 76 FR 31456 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ... Model GVI airplane will be an all-new, two- engine jet transport airplane with an executive cabin... Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification..., Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  16. 75 FR 26148 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-11

    ... Directives; The Boeing Company Model 737-100 and - 200 Series Airplanes AGENCY: Federal Aviation... 737-100 and -200 series airplanes. That action would have superseded an existing AD that requires... added inspections for certain airplanes, revised certain compliance times for all airplanes, and added...

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

    NASA Technical Reports Server (NTRS)

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

    1975-01-01

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

  18. 76 FR 56286 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, Model A330...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-13

    ...-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... were also performed on some rudders fitted on A330 and A340-200/-300 aeroplanes. An extended...

  19. 77 FR 75071 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Electrical/Electronic Equipment Bay...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-19

    ..., ANM-112, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes..., 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service....

  20. 77 FR 69569 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Pitch and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes... /M MO for emergency descent. Spiral stability must not restrict attaining roll angles up to 65...

  1. 76 FR 432 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes; Airbus...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ...-201, -202, -203, - 223, and -243 Airplanes; Airbus Model A330-300 Series Airplanes; and Airbus Model A340-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department...

  2. 75 FR 60655 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes; Airbus...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-01

    ...-201, -202, -203, - 223, and -243 Airplanes; Airbus Model A330-300 Series Airplanes; and Airbus Model A340-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION:...

  3. 75 FR 20265 - Airworthiness Directives; Liberty Aerospace Incorporated Model XL-2 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-19

    ... Aerospace Incorporated Model XL-2 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Liberty Aerospace Incorporated Model XL-2 airplanes. AD 2009-08-05 currently requires repetitively... approved the incorporation by reference of Liberty Aerospace, Inc. Service Document Critical...

  4. 78 FR 14007 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Electrical/Electronic Equipment Bay...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-04

    ... Systems Branch, ANM-112, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue...-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes designed for..., 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service....

  5. 78 FR 11555 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ... Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW...-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes designed for... airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft,...

  6. Design Oriented Structural Modeling for Airplane Conceptual Design Optimization

    NASA Technical Reports Server (NTRS)

    Livne, Eli

    1999-01-01

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

  7. 75 FR 15328 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... NPRM to add other airplane models to the applicability of the NPRM. We agree that suspect low-pressure... Model 757 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Model 757 airplanes. This AD...

  8. 76 FR 721 - Airworthiness Directives; Gulfstream Aerospace Corporation Model G-1159 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-06

    ... Aerospace Corporation Model G-1159 Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Proposed... Aerospace Corporation Model G-1159 airplanes. The existing AD requires an inspection to detect cracks or... (AD), applicable to Gulfstream Aerospace Corporation Model G- 1159 airplanes, was published in...

  9. 76 FR 71865 - Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane; Windshield Coating in...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-21

    ... Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace Corporation, Model GVI Airplane... Aerospace Corporation Model GVI airplane. This airplane will have a novel or unusual design feature(s..., Gulfstream Aerospace Corporation (GAC) applied for an FAA type certificate for its new Model GVI...

  10. 78 FR 75453 - Special Conditions: Cessna Model 750 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-12

    ... data network and design integration may result in security vulnerabilities from intentional or... than previous airplane models. This may allow the exploitation of network security vulnerabilities and... Airplanes; Aircraft Electronic System Security Isolation or Protection From Internal Access AGENCY:...

  11. 76 FR 36861 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... airplane models. This may allow the exploitation of network security vulnerabilities and increase risks... potential security vulnerabilities which could be exploited by unauthorized access to airplane networks and...; Electronic Systems Security Isolation or Protection From Unauthorized Passenger Systems Access...

  12. 76 FR 6578 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-07

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

  13. 76 FR 35736 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane Automatic Power Reserve...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-20

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

  14. 76 FR 39763 - Special Conditions: Boeing Model 787-8 Airplane; Interaction of Systems and Structures...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-07

    ... Administration 14 CFR Part 25 Special Conditions: Boeing Model 787-8 Airplane; Interaction of Systems and...: Federal Aviation Administration (FAA), DOT. ACTION: Amended special conditions SUMMARY: These amended special conditions are issued to the Boeing Model 787-8 airplane. This airplane will have novel or...

  15. 76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-20

    ... GIV-X Airplane; Aircraft Electronic System Security Protection From Unauthorized External Access..., ANM-111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton... configuration in the Gulfstream Model GIV-X passenger airplane. The Gulfstream Model GIV-X is a two-engine...

  16. 75 FR 48281 - Airworthiness Directives; The Boeing Company Model 737-900ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-10

    ... directive (AD) for certain Model 737-900ER series airplanes. This proposed AD would require doing a one-time... Directives; The Boeing Company Model 737-900ER Series Airplanes AGENCY: Federal Aviation Administration (FAA...-300ER series airplanes. The fuel tank access door at this location has a fuel measuring stick installed...

  17. 75 FR 71353 - Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. Various Models MU-2B Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-23

    ... Industries, Ltd. Various Models MU-2B Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... September 24, 1986, of the MU-2B-60 airplane flight manual (AFM) in table 3 of the Compliance section (e)(1... certain MHI various Models MU-2B airplanes. As published, table 3 specific to the MHI MU-2B-60...

  18. 76 FR 53305 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ...-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... applicability in the MCAI also identifies Airbus Model A340-200, -300, -500, and -600 series airplanes, this AD only applies to Airbus Model A330-200 and -300 series airplanes. FAA AD 2011-04-06, Amendment...

  19. 75 FR 47199 - Airworthiness Directives; McDonnell Douglas Corporation Model DC-9-10 Series Airplanes, DC-9-30...

    Federal Register 2010, 2011, 2012, 2013, 2014

    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 series...

  20. 75 FR 38941 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-07

    ... certain Learjet Inc. Model 45 airplanes. This proposed AD would require replacing aluminum fire... extinguisher container and damage to an aluminum discharge tube. Investigation revealed that following the... received a report of accidental discharge of a fire extinguisher container and damage to an aluminum...

  1. McDonnell F4-H1 Airplane Rocket Model

    NASA Image and Video Library

    1957-12-23

    L57-2809 Rocket model of McDonnell F4-H1 airplane on Terrier launcher with Nike booster, June 17, 1957. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 500.

  2. 76 FR 8319 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... application date to September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton,...

  3. 76 FR 10529 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Protection From...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... and access by external airplane sources and airline operations and maintenance systems to the aircraft... Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification... September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-20

    ... GIV-X Airplane; Isolation or Aircraft Electronic System Security Protection From Unauthorized Internal... passenger airplane. The Gulfstream Model GIV-X is a two-engine jet transport airplane with a maximum takeoff... navigation systems (aircraft control domain); 2. Airline business and administrative support...

  5. 76 FR 36870 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ..., FAA, Airframe/Cabin Safety Branch, ANM-115, Transport Standards Staff, Transport Airplane Directorate... date to September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet... Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  6. 76 FR 44245 - Special Conditions: Gulfstream Model GVI Airplane; Limit Engine Torque Loads for Sudden Engine...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-25

    ...-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton, Washington... Administration 14 CFR Part 25 Special Conditions: Gulfstream Model GVI Airplane; Limit Engine Torque Loads...

  7. 76 FR 8316 - Special Conditions: Gulfstream Model GVI Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... application date to September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton,...

  8. 76 FR 41041 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Interaction of Systems...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    .... and 4 p.m. FOR FURTHER INFORMATION CONTACT: Carl Niedermeyer, Transport Airplane Directorate, Aircraft.... Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910... Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane,...

  9. 76 FR 8314 - Special Conditions: Gulfstream Model GVI Airplane; Operation Without Normal Electric Power

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ..., Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue..., 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with a maximum passenger...

  10. 76 FR 9265 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System: Control...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-17

    ... Interface Branch, ANM-111, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification... September 28, 2006. The Gulfstream Model GVI airplane will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight will be 99,600 pounds, with a...

  11. 76 FR 36392 - Airworthiness Directives; Gulfstream Aerospace Corporation Model GV and GV-SP Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-22

    ... Aerospace Corporation Model GV and GV-SP Airplanes AGENCY: Federal Aviation Administration (FAA), DOT..., revising the limitations section of the airplane flight manual to add restrictions for APU usage for certain airplanes having a third fire extinguisher bottle, and removing the third fire extinguisher bottle...

  12. 76 FR 22828 - Airworthiness Directives; The Boeing Company Model 737-700 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-25

    ...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company Model 737-700 Series Airplanes AGENCY: Federal Aviation Administration (FAA... and defines fatigue loading of the airplane structure. On some airplanes, the passenger seat leg shear...

  13. Nonlinear-map model for the control of an airplane schedule

    NASA Astrophysics Data System (ADS)

    Nagatani, Takashi

    2013-12-01

    We study the dynamics and control of an airplane in air transportation between two airports. The dynamic models are presented for the airplane schedule. The dynamics of an airplane is described by the piecewise map and delayed map models. The characteristics of the nonlinear maps are studied analytically and numerically. The airplane displays the complex motion in the unstable region. The motion of the airplane depends on the quantity of goods, the control method, and the delay. It is shown that the control delay has an important effect on the motion.

  14. 77 FR 7007 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-10

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes; Model A330-300 series airplanes, Model A340-200 series airplanes; Model A340-300 series airplanes; Model A340-541 airplanes; and Model A340-642 airplanes. This proposed AD was prompted by reports...

  15. 78 FR 21037 - Special Conditions: Airbus Model A330-200 Airplanes; Bulk Cargo Lower Deck Crew Rest Compartments

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-09

    ...: Alan Sinclair, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft...-200 airplane. The Airbus Model A330-200 airplane is a wide-body, twin engine jet airplane. Operating... Aircraft Certification Service. Prior to operational use of a flight (cabin) crew rest compartment, the...

  16. 78 FR 76731 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ... Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057-3356... -300ER series airplanes. The Model 777-200 series airplanes are long-range, wide-body, twin-engine jet... airplanes with the ICG ePhone cordless cabin handset lithium ion battery installations. At present, there...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-01

    ... 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 of...

  18. 75 FR 47207 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-05

    ...-200 and -300 Series Airplanes, and Model A340-200, -300, -500 and -600 Series Airplanes AGENCY... Register on July 13, 2010. That AD applies to certain Model A330-200 and -300 series airplanes, and Model A340-200, -300, -500 and -600 series airplanes. A certain service bulletin number in Note 3 of...

  19. 76 FR 27872 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-13

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

  20. 75 FR 39863 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... Directives; Airbus Model A310 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... AD applies to all Airbus Model A310-203, -204, -221, - 222, -304, -322, -324, and -325 airplanes.... Table 3--Initial Inspection Internal Angle Model and configuration Compliance time (whichever occurs...

  1. 75 FR 22514 - Airworthiness Directives; The Boeing Company Model 747-200B Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-29

    ... side stringer 6 lap joints from STA 340 to STA 400. Since no U.S. Model 747-200B series airplanes are... Model 747-200B Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Model...

  2. 76 FR 62661 - Airworthiness Directives; The Boeing Company Model 767-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-11

    ... Model 767-200 and - 300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Model 767-200 and 767-300 series airplanes. This proposed AD would require installing cargo... (b) None. Applicability (c) This AD applies to The Boeing Company Model 767-200 and 767- 300...

  3. 78 FR 76734 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Seats...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ...: Alan Sinclair, FAA, Airplane and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft...- series airplanes are swept-wing monoplanes with a pressurized cabin. They share an identical supplier... is 41,000 feet for both model airplanes. The interior arrangements of the C-series airplanes...

  4. 76 FR 5505 - Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-01

    ... Model 777-200 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... Model 777-200 series airplanes. This proposed AD would require installing a new circuit breaker, relays... for the CSCP, ZMU, passenger address controller, cabin interphone controller, CACP, speaker...

  5. 76 FR 20501 - Airworthiness Directives; Fokker Services B.V. Model F.27 Mark 050 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-13

    ... Services B.V. Model F.27 Mark 050 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of.... Applicability (c) This AD applies to Fokker Services B.V. Model F.27 Mark 050 airplanes; certificated in any... and consequent loss of the aeroplane. Compliance (f) You are responsible for having the...

  6. 76 FR 27880 - Airworthiness Directives; DASSAULT AVIATION Model MYSTERE-FALCON 50 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-13

    ... Model MYSTERE-FALCON 50 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-Falcon 50 aeroplanes in service, it was detected that two pipes of the emergency brake system 2 located... applies to DASSAULT AVIATION Model MYSTERE-FALCON 50 airplanes, certificated in any category, all serial...

  7. 76 FR 13069 - Airworthiness Directives; BAE Systems (Operations) Limited Model ATP Airplanes; BAE Systems...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-10

    ... (Operations) Limited Model ATP Airplanes; BAE Systems (Operations) Limited Model HS 748 Airplanes AGENCY... specified products. The MCAI states: Early in the life of the ATP (circa 1989), a report was received that a... by issuing SB ATP- 27-11, describing a one-time inspection of the hinge pins, which was...

  8. 75 FR 82219 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    .... Models AT-802 and AT- 802A Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. That AD currently requires you to... spar lower caps at the center splice joint for cracks and repair or replace any cracked spar,...

  9. 77 FR 20520 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-05

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), Department... (AD) for all Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by... AD applies to all Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated in any...

  10. 78 FR 6198 - Special Conditions: Airbus, Model A318-112 Airplane (S/N 3238); Certification of Cooktops

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-30

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A318-112 Airplane (S/N..., serial number (S/N) 3238. This airplane, as modified by Fokker Services B.V., will have a novel or... certificate for an interior conversion on an Airbus Model A318-112 airplane, S/N 3238. The Airbus Model A318...

  11. 76 FR 10288 - Airworthiness Directives; The Boeing Company Model 767-200, -300, -300F, and -400ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-24

    ... Model 767-200, -300, -300F, and -400ER Series Airplanes AGENCY: Federal Aviation Administration (FAA... airworthiness directive (AD) that applies to The Boeing Company Model 767-200, -300, and -300F series airplanes..., October 5, 2005), for certain Model 767-200, -300, and -300F series airplanes. That AD...

  12. Estimated Flying Qualities of the Martin Model 202 Airplane

    NASA Technical Reports Server (NTRS)

    Weil, Joseph; Spear, Margaret

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

  14. 78 FR 14005 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Pitch and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-04

    .... The Model EMB-550 airplane is the first of a new family of jet airplanes designed for corporate flight... avoidance capability or with attaining and maintaining speeds near V MO /M MO for emergency descent. Spiral...

  15. 77 FR 69572 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: High Speed...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    .... The Model EMB-550 airplane is the first of a new family of jet airplanes designed for corporate flight...: Operation of the high speed limiter during all routine and descent procedure flight must not impede normal...

  16. 75 FR 21528 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-26

    ... certain Model MD-90-30 airplanes. This proposed AD would require inspecting for corrosion of the retract... system. We are proposing this AD to prevent corrosion and damage that could compromise the integrity of... Corporation MD-80 series airplanes. This condition, if not corrected, could result in corrosion and...

  17. 75 FR 81 - Special Conditions: Boeing Model 787-8 Airplane; Overhead Flightcrew Rest Compartment Occupiable...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... jet transport airplane with a two-aisle cabin. The maximum takeoff weight will be 476,000 pounds, with..., Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton, Washington... [Docket No. NM411 Special Conditions No. 25-09-07-SC] Special Conditions: Boeing Model 787-8...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-17

    ...-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton... application date to October 1, 2006. The 787 will be an all-new, twin- engine jet transport airplane with a... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Boeing Model 787 Series...

  19. 76 FR 35336 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-17

    ... by (1) reports of fuel leaks from certain drain locations of the slat track housing near the engine... engine exhaust nozzle, which could result in a fire when the airplane is stationary, or taxiing at low... Model 767 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We...

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

    NASA Technical Reports Server (NTRS)

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

    1959-01-01

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

  1. 78 FR 76772 - Special Conditions: Airbus Model A350-900 Airplanes; Permanently Installed Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ...This action proposes special conditions for Airbus Model A350- 900 series airplanes. These airplanes will have a novel or unusual design feature associated with permanently installed rechargeable lithium-ion batteries and battery systems. These batteries have certain failure, operational, and maintenance characteristics that differ significantly from those of the nickel-cadmium and lead-acid......

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-22

    ... airplanes. This proposed AD would require repetitive inspections for corrosion and cracking in the front... Model 757 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... side link support fitting at WS 292. We are proposing this AD to detect and correct such corrosion...

  3. 78 FR 76254 - Special Conditions: Airbus, Model A350-900 Series Airplane; Control Surface Awareness and Mode...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ... 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...

  4. 77 FR 57039 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  5. 76 FR 64857 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated in any category, serial numbers... (Challenger 300) airplanes, this AD applies to serial numbers 20003 and subsequent. This difference has been...

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

    NASA Technical Reports Server (NTRS)

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

    1997-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Redin, P. C.

    1981-01-01

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

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-09

    ... 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...

  9. 75 FR 2434 - Special Conditions: Boeing Model 747-8/-8F Series Airplanes; Design Roll Maneuver Requirement

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-15

    ... CONTACT: Todd Martin, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate...-8 and the Model 747-8F are four-engine jet transport airplanes that will have a maximum takeoff..., Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  10. 76 FR 38550 - Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable Length Escape Slide

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-01

    ..., FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification... a derivative of the 747-400. The Model 747-8 is a four-engine jet transport airplane that will have... airplane is immobilized on the ground. (b) There must be a positive means for the cabin crew to...

  11. 76 FR 44246 - Special Conditions: Boeing Model 747-8 Series Airplanes; Overhead Flight Attendant Rest Compartment

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-25

    ...-115, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601... the 747-400. The Model 747-8 is a four-engine jet transport airplane that will have a maximum takeoff... airplanes, crew rest compartments have been installed and certified in the main passenger cabin area,...

  12. 76 FR 14819 - Special Conditions: Boeing Model 747-8 Series Airplanes; Stairway Between the Main Deck and Upper...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-18

    ... Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind... 747-8 is a derivative of the 747-400. The Model 747-8 is a four-engine jet transport airplane that... located near door 2 on the main deck of the airplane in the forward part of the cabin. With large...

  13. 78 FR 25846 - Special Conditions: Airbus, Model A340-600 Series Airplanes; Lower Deck Crew Rest Compartments

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-03

    ... Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue.... The LDCR is located under the passenger cabin floor of Airbus Model A340-600 series airplanes and... Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  14. 76 FR 31451 - Special Conditions: Boeing Model 747-8 Airplanes; Stairway Between the Main Deck and Upper Deck

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ... Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton, Washington 98057- 3356... the 747-400. The Model 747-8 is a four-engine jet transport ] airplane that will have a maximum... deck of the airplane in the forward part of the cabin. With large seating capacities on the main...

  15. 75 FR 39 - Special Conditions: Boeing Model 757 Series Airplanes; Seats With Non-Traditional, Large, Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... issued for Boeing Model 757 series airplanes. These airplanes, as modified by Continental Airlines, Inc... CONTACT: John Shelden, FAA, Airframe/Cabin Safety Branch, ANM-115, Transport Airplane Directorate... flammability standards required of large, non-metallic panels in the cabin interior. At the time the...

  16. 77 FR 64023 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Roll...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-18

    ... modification 160023 (Sharklet). These airplanes will have novel or unusual design features when compared to the... 160023 on Model A321 series airplanes for the installation of a ``Sharklet,'' a large wingtip device. The... series airplanes with modification 160023 (Sharklet) and later derivatives because the existing special...

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

    NASA Astrophysics Data System (ADS)

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

    2016-01-01

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

  18. 76 FR 41657 - Airworthiness Directives; Airbus Model A330-342 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ...-249-AD; Amendment 39-16745; AD 2011-14-10] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330.... Applicability (c) This AD applies to Airbus Model A330-342 airplanes, manufacturer serial numbers (MSN) 0012 and...

  19. 75 FR 9809 - Airworthiness Directives; Airbus Model A330-243, -341, -342, and -343 Airplanes; and Model A340...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-04

    ... Directives; Airbus Model A330-243, -341, -342, and -343 Airplanes; and Model A340-541 and -642 Airplanes... Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send... retention bolts in order to detect any broken or missing bolts. This AD, which supersedes EASA AD...

  20. 75 FR 43878 - Airworthiness Directives; DASSAULT AVIATION Model Falcon 10 Airplanes; Model FAN JET FALCON, FAN...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-27

    .... List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed... this AD, certificated in any category. (1) DASSAULT AVIATION Model Falcon 10 airplanes, Model FAN JET... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; DASSAULT AVIATION...

  1. 76 FR 29673 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200 and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-23

    ... Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200 and -300 Series Airplanes... Service Bulletins A330-92-3077, Revision 01, dated March 29, 2010 (for Model A330-200 and -300 series airplanes); and A340-92-4078, Revision 01, dated April ] 9, 2010 (for Model A340-200 and -300...

  2. 76 FR 54093 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-31

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help...

  3. 76 FR 64847 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... information identified in this proposed AD, contact Bombardier, Inc., Q-Series Technical Help Desk,...

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

    NASA Technical Reports Server (NTRS)

    Hanson, P. W.

    1973-01-01

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

  5. 75 FR 46861 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-04

    ...-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental... revised the applicability statement of this supplemental NPRM to remove the Airbus Model A340-200,...

  6. 78 FR 63845 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Isolation or Airplane Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ... networks and systems, such as passenger entertainment and information services, than previous Embraer... unauthorized wired or wireless electronic connections between airplane systems and networks and the passenger...; Isolation or Airplane Electronic System Security Protection From Unauthorized Internal Access AGENCY...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-21

    ...-200 and -300 Series Airplanes, and Model A340-300 Series Airplanes AGENCY: Federal Aviation... accomplishing the actions specified in the NPRM (for Model A340-300 series airplanes). We have revised... information for accomplishing the actions specified in the NPRM (for Model A330-200 and A330-300...

  8. 78 FR 75284 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-11

    ..., Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P ... Inc., Models BD-500-1A10 and BD- 500-1A11 Series Airplanes; Flight Envelope Protection: High Speed...-1A11 series airplanes. These airplanes will have a novel or unusual design feature associated with...

  9. Simulation model of a twin-tail, high performance airplane

    NASA Technical Reports Server (NTRS)

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

    1992-01-01

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

  10. 75 FR 66651 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, and Model...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-29

    ...-201, -202, -203, - 223, and -243 Airplanes, and Model A330-300 Series Airplanes AGENCY: Federal...: An A330 experienced an uncommanded engine 1 in flight spool down, which occurred while applying fuel... scenarios, can lead to fuel starvation on the affected engine(s). * * * * * * * * We are issuing this AD to...

  11. 75 FR 59658 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  12. 75 FR 16660 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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,...

  13. 75 FR 30272 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  14. 76 FR 4216 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    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,...

  16. 75 FR 89 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

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

  17. 75 FR 13239 - Airworthiness Directives; SOCATA Model TBM 700 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

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

    NASA Technical Reports Server (NTRS)

    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.

  19. 76 FR 66660 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-27

    ...This action proposes special conditions for the Gulfstream Aerospace LP (GALP) Model G280 airplane. This airplane will have a novel or unusual design feature associated with operation without normal electrical power. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

  20. 77 FR 62182 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-12

    ... Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Airbus Model A310 series airplanes. This proposed...

  1. 77 FR 42952 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-23

    ...-139-AD; Amendment 39-17127; AD 2012-14-13] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports of some...

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

    NASA Astrophysics Data System (ADS)

    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.

  3. Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane

    NASA Technical Reports Server (NTRS)

    Snyder, Thomas L.

    1947-01-01

    Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/35-scale model of the Douglas XB-43 airplane. The spin and recovery characteristics were determined for several loading conditions of the airplane. The effects of installing a dorsal fin and of installing a ventral fin were investigated. Emergency escape of the crew was simulated and the stick and rudder pedal forces necessary to effect recoveries on the airplane were determined.

  4. 75 FR 51701 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-23

    ... visual inspection for galling of the fuel supply manifold assembly, a general visual inspection for..., and corrective actions if necessary. The corrective actions include replacing the fuel supply manifold... airplanes, changing the routing and clamping configuration of the engine and alternator wire harnesses, and...

  5. AGATE concept model for a future general aviation airplane

    NASA Technical Reports Server (NTRS)

    1996-01-01

    Photo illustrates an advanced general aviation concept airplane. The pusher propeller - driven configuration seats 4 to 6 people (including pilot) in mid-wing, three-surface twin tail-boom configuration. The design concept incorporates natural laminar flow, ice protection, winglets and stall-departure-resistant flight dynamics.

  6. 76 FR 78524 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-19

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final... series airplanes, Model A340-200 and -300 series airplanes, and Model A340-500 and -600 series airplanes..., ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington...

  7. 78 FR 9581 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-11

    ...-052-AD; Amendment 39-17346; AD 2013-03-11] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes..., and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of cracking...

  8. 77 FR 59149 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-26

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes..., and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This proposed AD was prompted by reports of...

  9. Scaling behavior of an airplane-boarding model.

    PubMed

    Brics, Martins; Kaupužs, Jevgenijs; Mahnke, Reinhard

    2013-04-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1948-01-01

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

  11. 75 FR 52614 - Special Conditions: Embraer Model ERJ 170-100 SU Series Airplanes; Seats With Non-Traditional...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-27

    ... CONTACT: Jayson Claar, FAA, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 16501... Certificate (STC) for an interior modification to include seats with large, non- metallic panels in the cabin interior in the Embraer Model ERJ 170-100 SU series airplanes. The Model ERJ 170-100 SU, which is...

  12. 77 FR 70941 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-28

    ...., Model EMB-550 Airplane; Interaction of Systems and Structures AGENCY: Federal Aviation Administration... feature(s) associated with the interaction of systems and structures. The applicable airworthiness... primary structure is metal with composite empennage and control surfaces. The Model EMB-550 airplane...

  13. 76 FR 67343 - Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-01

    ... Model 737-300, -400, and -500 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive... investigative and corrective actions. This AD reduces the compliance times for those actions. This AD was...

  14. 78 FR 8961 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Hydrophobic Coatings in Lieu of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-07

    ... metal with composite empennage and control surfaces. The Model EMB-550 airplane is designed for 8... for normal takeoff. The primary flight controls consist of hydraulically powered fly-by-wire elevators, aileron and rudder, controlled by the pilot or copilot sidestick. The Model EMB-550 airplane will use...

  15. 75 FR 27668 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-18

    ... Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation... applies to Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, all... of the aeroplane during landing. * * * * * Compliance (f) You are responsible for having the...

  16. 75 FR 4485 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-28

    .... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in... with improved actuators. Actions and Compliance (f) Unless already done, do the following actions....

  17. 75 FR 35624 - Airworthiness Directives; Fokker Services B.V. Model F.27 Mark 500 and 600 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    .... Model F.27 Mark 500 and 600 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of.... Applicability (c) This AD applies to Fokker Services B.V. Model F.27 Mark 500 and 600 airplanes; certified in... landing roll. Compliance (f) You are responsible for having the actions required by this AD...

  18. 75 FR 64963 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-21

    .... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, equipped with... likely to follow. Compliance (f) You are responsible for having the actions required by this AD...

  19. 76 FR 8618 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    .... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, equipped with... follow. Compliance (f) You are responsible for having the actions required by this AD performed...

  20. 75 FR 3656 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-22

    ... Model 767-200, -300, and -300F Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Model 767-200, -300, and -300F series airplanes. This proposed AD would require inspecting to verify the part number of the low- pressure flex-hoses of the flightcrew and...

  1. 76 FR 7694 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-11

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

  2. 76 FR 46 - Airworthiness Directives; Airbus Model A310-203, -204, -222, -304, -322, and -324 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-03

    ...-203, -204, -222, - 304, -322, and -324 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... applies to Model A310-203, -204, -222, -304, -322, and -324 airplanes, certificated in any category, all... (whichever occurs later) Model A310-203, A310-204, and A310- 1 and 2 Prior to the Within 1,500 flight...

  3. 76 FR 41667 - Airworthiness Directives; Hawker Beechcraft Corporation Models B300 and B300C (C-12W) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION... Corporation Models B300 and B300C (C-12W) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... Corporation Models B300 and B300C (C-12W) airplanes. This AD was prompted by an error found in the...

  4. 76 FR 17758 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-31

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), Department... Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, having serial numbers (S/Ns) 20001 through..., ``Certification Maintenance Requirements,'' in Part 2 of Chapter 5 of Bombardier Challenger 300 BD-100 Time Limits...

  5. 75 FR 27406 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-17

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), Department... Maintenance Requirements,'' in Part 2 of Chapter 5 of Bombardier Challenger 300 BD- 100 Time Limits.... Applicability (c) This AD applies to Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, having...

  6. 75 FR 16646 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-02

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), Department.... Applicability (c) This AD applies to Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated... Bombardier Challenger 300 AFM, CSP 100-1, to include the information in Bombardier Temporary Revision TR-39...

  7. 76 FR 62669 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-11

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION..., ``Certification Maintenance Requirements,'' of Part 2, ``Airworthiness Limitations,'' of the Bombardier Challenger... all Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated in any category. Note...

  8. 76 FR 56680 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes; Model A340-200 and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-14

    ... Model A330-200 and -300 Series Airplanes; Model A340-200 and -300 Series Airplanes; Model A340-500 and... Date Model A330 AOT A330-26A3052 April 19, 2011. Model A340-200, -300 AOT A340-200/300-26A4044...-26A3052, dated April 19, 2011 (for Model A330-200 and -300 series airplanes); Airbus AOT...

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

    NASA Technical Reports Server (NTRS)

    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.

  10. 76 FR 20493 - Airworthiness Directives; Fokker Services B.V. Model F.27 Mark 050 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-13

    .... Model F.27 Mark 050 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of.... Affected ADs (b) None. Applicability (c) This AD applies to Fokker Services B.V. Model F.27 Mark 050... resulting in fuel leakage and, in combination with other factors, a fuel fire. Compliance (f) You...

  11. 75 FR 75870 - Airworthiness Directives; Airbus Model A300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-07

    ...-076-AD; Amendment 39-16536; AD 2010-25-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300... AD applies to Airbus Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 airplanes...

  12. 76 FR 20496 - Airworthiness Directives; Airbus Model A340-541 and -642 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-13

    ...-105-AD; Amendment 39-16653; AD 2011-08-03] RIN 2120-AA64 Airworthiness Directives; Airbus Model A340.... Applicability (c) This AD applies to Airbus Model A340-541 and -642 airplanes; certificated in any category; all...

  13. 78 FR 36084 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-17

    ... Federal Aviation Administration 14 CFR Part 23 Special Conditions: Cirrus Design Corporation Model SF50... notice granting special conditions for the Cirrus Design Corporation model SF50 airplane. We are withdrawing Special Condition No. 23-248-SC through mutual agreement with Cirrus Design Corporation. DATES...

  14. 75 FR 45075 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  15. 76 FR 9495 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-18

    .... Models AT-802 and AT- 802A Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final... Directive (AD) 2010-17-18, which applied to these products: Air Tractor, Inc. (Air ] Tractor) Models AT-802... at the center splice joint for cracks and repair or replace any cracked spar, and changes the...

  16. 75 FR 52255 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-25

    ...; AD 2010-17-18] RIN 2120-AA64 Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT- 802A... all Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. AD 2010-13-08 currently... both of the wing main spar lower caps at the center splice joint for cracks and repair or replace...

  17. 75 FR 35616 - Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    .... Models AT-802 and AT- 802A Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... supersede AD 2006-08-09, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A... two outboard fastener holes in both of the wing main spar lower caps at the center splice joint...

  18. 76 FR 62605 - Airworthiness Directives; Viking Air Limited Model DHC-3 (Otter) Airplanes With Supplemental Type...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-11

    ... 2011-CE-018-AD; Amendment 39-16709; AD 2011-12-02] RIN 2120-AA64 Airworthiness Directives; Viking Air... airworthiness directive (AD) that published in the Federal Register. That AD applies to Viking Air Limited Model... for Viking Air Limited Model DHC-3 (Otter) airplanes equipped with a Honeywell TPE331-10 or -12JR...

  19. 76 FR 28914 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-19

    ... of the rudder system design. Rudder pedal sensitivity on Model A300-600 and A310 series airplanes is greater than that of other transport category airplane designs. Such rudder control sensitivity could...

  20. 76 FR 5061 - Special Conditions: TTF Aerospace, LLC, Modification to Boeing Model 767-300 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-28

    ... INFORMATION CONTACT: John Shelden, FAA, Airframe/Cabin Safety Branch, ANM-115, Transport Airplane Directorate... Model 767-300 series airplanes is novel in that it will be located below the passenger cabin floor in... the cabin pressure altitude exceeds 15,000 feet. The aural warning must sound continuously for...

  1. 78 FR 68775 - Special Conditions: Airbus, Model A350-900 Series Airplane; Composite Fuselage In-Flight Fire...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-15

    ...: Jeff Gardlin, FAA, Airframe/Cabin Safety, ANM-115, Transport Airplane Directorate, Aircraft..., on November 12, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series...

  2. 77 FR 67251 - Special Conditions: Boeing Model 757 Series Airplanes; Seats with Non-Traditional, Large, Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-09

    ... Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue... more stringent flammability standards required of large, non-metallic panels in the cabin interior. At.... 25.853(c), Compartment interiors. For Boeing Model 757-300 series airplanes--part 25, as amended...

  3. 78 FR 11562 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: High Speed...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ...These special conditions are issued for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature, specifically an electronic flight control system which contains fly-by-wire control laws, including envelope protections, for the overspeed protection and roll limiting function. The applicable airworthiness regulations do not contain adequate or......

  4. 75 FR 67639 - Airworthiness Directives; Piaggio Aero Industries S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-03

    ... 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....

  5. 76 FR 69168 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-08

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes..., and B4-203 airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes....

  6. 78 FR 32078 - Special Conditions: Gulfstream Model G280 Airplane, Enhanced Flight Vision System (EFVS) With...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-29

    ...These special conditions are issued for the Gulfstream model G280 series airplanes. These airplanes, as modified by Gulfstream Aerospace Corporation, will have an advanced, enhanced-flight-vision system (EFVS). The EFVS is a novel or unusual design feature which consists of a head-up display (HUD) system modified to display forward- looking infrared (FLIR) imagery. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

  7. 76 FR 6549 - Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes, Model A300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-07

    ... 2010-NM-054-AD; Amendment 39-16595; AD 2011-03-11] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4- 600R Series Airplanes, Model A300 F4-605R Airplanes, and Model A300 C4- 605R...-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356...

  8. 78 FR 63847 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Airplane Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ...); 3. Passenger information and entertainment systems (passenger entertainment services); and, 4. The... business and administrative support systems, Passenger entertainment systems, and Access by systems...; Airplane Electronic System Security Protection From Unauthorized External Access AGENCY: Federal Aviation...

  9. 77 FR 32006 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-05-31

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Model GVI Airplane; High... pertaining to a high incidence protection system that replaces the stall warning system during normal.... (4) The center of gravity position that results in the highest value of reference stall speed....

  10. 76 FR 50 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-03

    ... 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; Airbus Model A310 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

  11. 76 FR 39035 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-05

    ... 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; Airbus Model A310 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

  12. 75 FR 24389 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-05

    .... Model DHC-8-400 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... pitot/static heater, engine adapter heater, and propeller heater. Failure of both AC generators would... could lead to unannunciated loss of heat to both engine inlets, which could lead to loss of power in...

  13. 76 FR 39256 - Airworthiness Directives; Dassault Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-06

    ... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation.... The MCAI describes the unsafe condition as: On some Falcon 7X aeroplanes, it has been determined...: On some Falcon 7X aeroplanes, it has been determined potential low clearance between electrical...

  14. 76 FR 8919 - Airworthiness Directives; DASSAULT AVIATION Model MYSTERE-FALCON 50 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-16

    ... Model MYSTERE-FALCON 50 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...: On two occurrences on Myst re-Falcon 50 aeroplanes in service, it was detected that two pipes of the... this proposed AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-01

    ... Model Mystere-Falcon 50 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...-Falcon 50 aeroplanes in service, it was detected that two pipes had been swapped in maintenance at the... condition for the specified products. The MCAI states: On two occurrences on Myst re-Falcon 50 aeroplanes in...

  16. 76 FR 12624 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-08

    ... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... product. The MCAI describes the unsafe condition as: On some Falcon 7X aeroplanes, it has been determined... this proposed AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606...

  17. 76 FR 31508 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... pressure bulkhead of SAAB 2000 aeroplanes, located on the rear side of the bulkhead at the bottom outboard...

  18. 76 FR 13072 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-10

    ...-145-AD; Amendment 39-16623; AD 2011-05-13] RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... upper cap of the horizontal stabilizer of SAAB 2000 aeroplanes. The affected areas are adjacent to the...

  19. 76 FR 41665 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ...-111-AD; Amendment 39-16747; AD 2011-14-12] RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... potentially unsafe condition, SAAB has published Service Bulletin (SB) 2000-32-073, describing a inspection of...

  20. 75 FR 77796 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-14

    ... TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... the rear spar upper cap of the horizontal stabilizer of SAAB 2000 aeroplanes. The affected areas are...

  1. 77 FR 58970 - Special Conditions: Embraer S.A. Model EMB-550 Airplanes, Sudden Engine Stoppage

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-25

    ... it relates to sudden engine-stoppage conditions. Type Certification Basis Under the provisions of.... Model EMB-550 Airplanes, Sudden Engine Stoppage AGENCY: Federal Aviation Administration (FAA), DOT... the effects of sudden engine stoppage upon the airframe. The applicable airworthiness regulations do...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-02

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault Aviation Model Mystere-Falcon 50 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...) originated by an aviation authority of another country to identify and correct an unsafe condition on...

  3. 75 FR 1697 - Airworthiness Directives; Dassault-Aviation Model Falcon 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-13

    ... Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2009-1252; Directorate Identifier 2009-NM-248-AD; Amendment 39-16173; AD 2010-02-02] RIN 2120-AA64 Airworthiness Directives; Dassault-Aviation Model Falcon 7X Airplanes AGENCY: Federal Aviation Administration (FAA), Department of...

  4. 75 FR 82327 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... an aviation authority of another country to identify and correct an unsafe condition on an...

  5. 76 FR 6535 - Airworthiness Directives; The Boeing Company Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-07

    ... fire handle shutoff relay circuit due to a lack of separation between engine wires. We are issuing this... affected airplane models. Conclusion We reviewed the relevant data and determined that air safety and the... that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by...

  6. 75 FR 5690 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-04

    ... 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;...

  7. 76 FR 21815 - Airworthiness Directives; The Boeing Company Model 737 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-19

    ... supplemental NPRM to prevent an undetected failure of the primary load path for the ballscrew in the drive mechanism of the HSTA and subsequent wear and failure of the secondary load path, which could lead to loss... actuator (HSTA) on a Model 757 airplane. Extensive corrosion of the primary load path ball bearings in...

  8. 76 FR 38062 - Airworthiness Directives; Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    ... Aerospace LP Model Galaxy and Gulfstream 200 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive..., West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590....

  9. 76 FR 61036 - Airworthiness Directives; Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-03

    ... Aerospace LP Model Galaxy and Gulfstream 200 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness... Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC....

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-05

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Model GVI Airplane; Limit..., the engine mounts and the supporting structures must be designed to withstand a ``limit engine torque load imposed by sudden engine stoppage due to malfunction or structural failure.'' Limit loads are...

  11. 75 FR 7945 - Airworthiness Directives; Augustair, Inc. Models 2150, 2150A, and 2180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-23

    ... reinforce the vertical stabilizer spar regardless if cracks are found. This AD results from six reports of....horsburgh@faa.gov . SUPPLEMENTARY INFORMATION: Discussion We received a maintenance problem report on an.... We have also received five additional reports of Augustair, Inc. Models 2150A and 2180 airplanes...

  12. 75 FR 6154 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-08

    ... repetitive detailed and high frequency eddy current (HFEC) inspections of the station (STA) 1809.5 bulkhead...), for all Model 767 airplanes. That AD requires repetitive detailed and high frequency eddy current... detailed and high frequency eddy current (HFEC) inspections for cracking as specified in Parts 1, 2, 3,...

  13. 75 FR 950 - Airworthiness Directives; The Boeing Company Model 777 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-07

    ... inspecting the slat cans at the outboard slat number 3 and 12 outboard main track locations for holes and... of a hole in the inboard main track slat can for outboard slat number 12 on a Model 777 airplane. The... can. We are proposing this AD to detect and correct damage to the outboard slat main track slat cans...

  14. 76 FR 55296 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-07

    .... Model DHC-8-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support... metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure...

  15. 75 FR 52290 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-25

    ... Directives; Bombardier, Inc. Model DHC-8-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA... found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support... sheet metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that...

  16. 75 FR 81420 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ..., Inc. Model DHC-8-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... support brackets that were manufactured using sheet metal have been found cracked on DHC-8 Series 300... been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the...

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

    NASA Technical Reports Server (NTRS)

    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.

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Windham, John O.

    1950-01-01

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

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

    NASA Technical Reports Server (NTRS)

    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.

  20. 76 FR 291 - Special Conditions: Gulfstream Model GVI Airplane; Single-Occupant Side-Facing Seats

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-04

    ... all-new, two-engine jet transport airplane with an executive cabin interior. The maximum takeoff... Branch, ANM-115, Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification... Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  1. 76 FR 14795 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-18

    ...-new, two- engine jet transport airplane with an executive cabin interior. The maximum takeoff weight... Standards Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW..., Washington, on March 9, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft...

  2. 75 FR 20518 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Full Authority Digital Engine...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-20

    ... Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust... Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P ... Airplane; Full Authority Digital Engine Control (FADEC) System AGENCY: Federal Aviation Administration...

  3. 76 FR 27227 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-11

    ... Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT...-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356... airplane configuration: Cold working of trellis boom drainage holes. Repetitive detailed or rotating...

  4. 77 FR 49705 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-17

    .... SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports that some...

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.

    1948-01-01

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

  6. 76 FR 3854 - Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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,...

  7. 78 FR 26716 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-08

    ... A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. The existing AD... would expand the applicability, reduce the compliance ] time, change torque values of the check valve... on Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes...

  8. 78 FR 59295 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-26

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... Model A330-201, -202, -203, -223, - 223F, -243, and -243F Airplanes, Model A330-300 series airplanes, and Model A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2010-23-12...

  9. The Air Forces on a Model of the Sperry Messenger Airplane Without Propeller

    NASA Technical Reports Server (NTRS)

    Munk, Max M; Diehl, Walter S

    1926-01-01

    This is a report on a scale effect research which was made in the variable-density wind tunnel of the National Advisory Committee for Aeronautics at the request of the Army Air Service. A 1/10 scale model of the sperry messenger airplane with USA-5 wings was tested without a propeller at various Reynolds numbers up to the full scale value. Two series of tests were: the first on the original model which was of the usual simplified construction, and the second on a modified model embodying a great amount of detail. The experimental results show that the scale effect is almost entirely confined to the drag. It was also found that the model should be geometrically similar to the full-scale airplane if the test data are to be directly applicable to full scale.

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

    NASA Technical Reports Server (NTRS)

    Kolb, Mark A.

    1990-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Becker, John V; LEONARD LLOYD H

    1942-01-01

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

  12. 75 FR 9515 - Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-03

    ...-16202; AD 2010-04-09] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 Series Airplanes and Model A340-200 and -300 Series Airplanes Correction In rule document 2010-3119 beginning on page 7940...

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

    NASA Technical Reports Server (NTRS)

    Brandon, Jay M.; Foster, John V.

    1998-01-01

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

  14. 78 FR 73993 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-10

    ... design feature associated with the architecture and connectivity capabilities of the airplanes' computer... vulnerabilities to the airplanes' systems. The proposed network architecture includes the following connectivity... architecture is novel or unusual for executive jet airplanes by allowing connection to airplane electronic...

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; McBride, Ellis E.

    1954-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Morris, Garland J.

    1948-01-01

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

  17. 76 FR 63822 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Limit Engine Torque Loads...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-14

    ...These special conditions are issued for the Gulfstream Aerospace LP (GALP) model G280 airplane. This airplane will have a novel or unusual design feature associated with engine torque loads imposed by sudden engine stoppage. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

  18. 76 FR 39248 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-06

    ..., Revision 02, dated June 10, 2010 (for Model A310 series airplanes). (1) If missing pipes, distortions, or...-044-AD; Amendment 39-16736; AD 2011-14-01] RIN 2120-AA64 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes...

  19. 76 FR 22059 - Airworthiness Directives; The Boeing Company Model 757 Airplanes, and Model 767-200, 767-300, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-20

    ... the audio accessory unit, replacing certain handsets and EICAS computers, changing EICAS computer... Bulletin Affected airplanes Changing wires from the Boeing Service Model 767-200 and - audio accessory unit... wires from the audio accessory unit (AAU) on the E2-5 shelf to the bell chime module in the warning...

  20. 77 FR 63716 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-17

    ...-180-AD; Amendment 39-17213; AD 2012-20-07] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... -112 airplanes; and all Model A319, A320, and A321 series airplanes. That AD currently requires... incorporate revised fuel maintenance and inspection tasks, and adds airplanes to the applicability. This...

  1. 77 FR 48427 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-14

    ...-209-AD; Amendment 39-17153; AD 2012-16-06] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... airplanes and Model A310-203, -204, - 221, and -222 airplanes. This AD was prompted by a report of a... loss of the airplane. DATES: This AD becomes effective September 18, 2012. The Director of the...

  2. 77 FR 60325 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-03

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... series airplanes. For certain airplanes, that NPRM proposed repetitive inspections for cracks of the... Model 318 airplanes from the applicability. That NPRM was prompted by reports of cracks found in...

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

    NASA Technical Reports Server (NTRS)

    Parkinson, R. C. H.

    1983-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1981-01-01

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

  5. Further comparison of wind tunnel and airplane acoustic data for advanced design high speed propeller models

    NASA Astrophysics Data System (ADS)

    Dittmar, J. H.

    Comparisons were made between the SR-2 and SR-3 model propeller noise data taken in the NASA 8-by-6 wind tunnel, in the United Technologies Research Center (UTRC) anechoic tunnel, and with boom and fuselage microphones on the NASA Jetstar airplane. Plots of peak blade passage tone noise versus helical tip Mach number generally showed good agreement. The levels of the airplane fuselage data were somewhat lower than the boom data by an approximately uniform value. The curve shapes were similar except for the UTRC data which was flatter than the other sets. This was attributed to the UTRC data being taken at constant power while the other data were taken at constant advance ratio. General curves of the peak blade passage tone versus helical tip Mach number fit through all the data are also presented. Directivity shape comparisons at the cruise condition were similar for the airplane and 8-by-6 tunnel data. The UTRC data peaked farther forward but, when an angle correction was made for the different axial Mach number used in the UTRC tests, the shape was similar to the others. The general agreement of the data from the four configurations enables the formation of a good consensus of the noise from these propellers.

  6. Further comparison of wind tunnel and airplane acoustic data for advanced design high speed propeller models

    NASA Technical Reports Server (NTRS)

    Dittmar, J. H.

    1985-01-01

    Comparisons were made between the SR-2 and SR-3 model propeller noise data taken in the NASA 8-by-6 wind tunnel, in the United Technologies Research Center (UTRC) anechoic tunnel, and with boom and fuselage microphones on the NASA Jetstar airplane. Plots of peak blade passage tone noise versus helical tip Mach number generally showed good agreement. The levels of the airplane fuselage data were somewhat lower than the boom data by an approximately uniform value. The curve shapes were similar except for the UTRC data which was flatter than the other sets. This was attributed to the UTRC data being taken at constant power while the other data were taken at constant advance ratio. General curves of the peak blade passage tone versus helical tip Mach number fit through all the data are also presented. Directivity shape comparisons at the cruise condition were similar for the airplane and 8-by-6 tunnel data. The UTRC data peaked farther forward but, when an angle correction was made for the different axial Mach number used in the UTRC tests, the shape was similar to the others. The general agreement of the data from the four configurations enables the formation of a good consensus of the noise from these propellers.

  7. Noise-reduction measurements of stiffened and unstiffened cylindrical models of an airplane fuselage

    NASA Technical Reports Server (NTRS)

    Willis, C. M.; Mayes, W. H.

    1984-01-01

    Noise-reduction measurements are presented for a stiffened and an unstiffened model of an airplane fuselage. The cylindrical models were tested in a reverberant-field noise environment over a frequency range from 20 Hz to 6 kHz. An unstiffened metal fuselage provided more noise reduction than a fuselage having the same sidewall weight divided between skin and stiffening stringers and ring frames. The addition of acoustic insulation to the models tended to smooth out the interior-noise spectrum by reducing or masking the noise associated with the structural response at some of the resonant frequencies.

  8. 75 FR 77569 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Flight Control System Mode...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-13

    ... will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum... Standards Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW..., Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  9. 78 FR 64415 - Special Conditions: Airbus, Model A350-900 Series Airplane; Ground Pivoting Loads

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-29

    ...: Todd Martin, FAA, Airframe/Cabin Safety, ANM-115, Transport Airplane Directorate, Aircraft... series airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR part 25 Aircraft..., Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  10. 75 FR 75 - Special Conditions: Boeing Model 787-8 Airplane; Overhead Crew Rest Compartment

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... jet transport airplane with a two-aisle cabin. The maximum takeoff weight will be 476,000 pounds, with... Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton...-8 airplanes with an overhead crew rest (OCR) compartment installed above the main passenger...

  11. 75 FR 29962 - Special Conditions: Cirrus Design Corporation Model SF50 Airplane; Function and Reliability Testing

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-28

    ... Airplane Directorate, Aircraft Certification Service, 901 Locust, Room 301, Kansas City, MO 64106... part 23 aircraft. Additionally, part 23 airplanes are being used for business and commercial... Kansas City, Missouri on May 18, 2010. John Colomy, Acting Manager, Small Airplane Directorate,...

  12. 75 FR 39189 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-08

    ... airplanes. This proposed AD would require repetitive inspections for cracking in the body skin around the aft corners of the nose wheel well; for certain airplanes, repetitive inspections for cracking in the... cracking in the body skin and the skin splice plate; for certain airplanes, an inspection for steel...

  13. 78 FR 63848 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Sidestick Controllers

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ...; Sidestick Controllers AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special condition... airplane. This airplane will have a novel or unusual design feature associated with sidestick controllers... airplane will use passive sidestick controllers for pitch and roll control instead of a conventional...

  14. Amphibious Airplane

    NASA Technical Reports Server (NTRS)

    1986-01-01

    The airplane pictured is the new Air Shark I, a four-place amphibian that makes extensive use of composite materials and cruises at close to 200 miles per hour under power from a 200-horsepower engine. Air Shark I is a "homebuilt" airplane, assembled from a kit of parts and components furnished by Freedom Master Corporation, Satellite Beach, Florida. The airplane incorporates considerable NASA technology and its construction benefited from research assistance provided by Kennedy Space Center (KSC) In designing the Shark, company president Arthur M. Lueck was able to draw on NASA's aeronautical technology bank through KSC's computerized "recon" library. As a result of his work at KSC, the wing of the Air Shark I is a new airfoil developed by Langley Research Center for light aircraft. In addition, Lueck opted for NASA-developed "winglets," vertical extensions of the wing that reduce drag by smoothing air turbulence at the wingtips. The NASA technology bank also contributed to the hull design. Lueck is considering application of NASA laminar flow technology-means of smoothing the airflow over wing and fuselage-to later models for further improvement of the Shark's aerodynamic efficiency. A materials engineer, Lueck employed his own expertise in designing and selecting the materials for the composite segments, which include all structural members, exposed surfaces and many control components. The materials are fiber reinforced plastics, or FRP They offer a high strength-to-weight ratio, with a nominal strength rating about one and a half times that of structural steel. They provide other advantages: the materials can be easily molded into finished shapes without expensive tooling or machining, and they are highly corrosion resistant. The first homebuilt to be offered by Freedom Master, Air Shark I completed air and water testing in mid-1985 and the company launched production of kits.

  15. Spin-Tunnel Investigation of the Spinning Characteristics of Typical Single-Engine General Aviation Airplane Designs. 1. Low-Wing Model A: Effects of Tail Configurations

    NASA Technical Reports Server (NTRS)

    Burk, S. M., Jr.; Bowman, J. S., Jr.; White, W. L.

    1977-01-01

    The effects of tail design on spin and recovery were investigated in a spin tunnel. A 1/11-scale model of a research airplane which represents a typical low-wing, single engine, light general aviation airplane was used. A tail design criterion for satisfactory spin recovery for light airplanes was evaluated. The effects of other geometric design features on the spin and recovery characteristics were also determined. Results indicate that the existing tail design criterion for light airplanes, which uses the tail damping power factor as a parameter, cannot be used to predict spin-recovery characteristics.

  16. 75 FR 7407 - Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-19

    ... 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 V...

  17. 75 FR 61977 - Airworthiness Directives; The Boeing Company Model 747-100, 747-200B, and 747-200F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

    ... Model 747-100, 747- 200B, and 747-200F Series Airplanes AGENCY: Federal Aviation Administration (FAA... airworthiness directives (ADs), which apply to certain Model 747-100, 747-200B, and 747-200F series airplanes... the skin panel lap joints in the fuselage upper lobe, and repair if necessary. One of the existing...

  18. AIRCL: A programmed system for generating NC tapes for airplane models. User's manual

    NASA Technical Reports Server (NTRS)

    Akgerman, N.; Billhardt, C. F.

    1981-01-01

    A computer program is presented which calculates the cutter location file needed to machine models of airplane wings or wing-fuselage combinations on numerically controlled machine tools. Input to the program is a data file consisting of coordinates on the fuselage and wing. From this data file, the program calculates tool offsets, determines the intersection between wing and fuselage tool paths, and generates additional information needed to machine the fuselage and/or wing. Output from the program can be post processed for use on a variety of milling machines. Information on program structure and methodology is given as well as the user's manual for implementation of the program.

  19. Spin Investigation of a 1/29-Scale Model of the Republic XF-91 Airplane with a Conventional Tail Installed

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.; Jones, Ira P., Jr.

    1949-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/29-scale model of the Republic XF-91 airplane with a.conventional-tail arrangement installed. Previously, tests were made on the model with a vee tail installed. The erect spin and recovery characteristics of the model were determined for the normal loading with the wing installed at various amounts of incidence. The spin investigation also included inverted-spin tests, spin-recovery-parachute tests, tests with the center of gravity moved rearward, and tests with external fuel tanks added to the model. In addition, several tail.modifications were tested,on the model in an attempt, to improve the model's spin-recovery characteristics. The results indicate that any fully developed spin obtained on the airplane with the conventional tail installed will be satisfactorily terminated if rudder reversal is accompanied by moving the ailerons with the spin (stick right in a right spin).Decreasing the wing incidence from 6deg to -2deg should have a beneficial effect on the recovery characteristics of the airplane. Recovery characteristics by normal use of controls (full rudder reversal followed by moving the elevators down) will be satisfactory if the wing incidence,of the airplane is -2deg. Installation of external fuel tanks (with or without fuel) will have a somewhat adverse effect on the recovery characteristics of the airplane, but if the recovery technique includes movement of the ailerons to full with the spin, the spin rotation will be terminated rapidly. Varying the position of the center of gravity within the limits indicated to be possible on the airplane should not affect the recovery characteristics.

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

    NASA Technical Reports Server (NTRS)

    Pepper, Edward; Foster, Gerald V.

    1946-01-01

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

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

    SciTech Connect

    Steffen, Jason H.; /Fermilab

    2008-08-01

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

  2. Aerodynamic Characteristics of a Canard and an Outboard-Tail Airplane Model at High Subsonic Speeds

    NASA Technical Reports Server (NTRS)

    Fournier, Paul G.

    1961-01-01

    An investigation has been made in the Langley high-speed 7- by 10-foot tunnel through a range of Mach numbers from 0.60 to 0.95 of the static longitudinal and lateral stability and control characteristics of a canard airplane configuration and an outboard-tail configuration. The canard model had a twisted wing with approximately 67 deg of sweepback and an aspect ratio of 2.91 and was tested with three trapezoidal canard surfaces having ratios of exposed area to wing area of 0.032, 0.076, and 0.121. The canard model had a single body-mounted vertical tail. The outboard-tail model had its horizontal- and vertical-tail surfaces mounted on slender bodies attached to the wing tips and located to the rear and outboard of the 67 deg sweptback wing of aspect ratio 1.00. The data, which are presented with limited analysis, provide information at high subsonic speeds on these two types of high-speed airplanes which have previously been tested at supersonic speeds and reported in NACA RM L58BO7 and NACA RM L58E20.

  3. 78 FR 28152 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-14

    ...: We propose to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A318-111 and -112 airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321... relevant data, views, or arguments about this proposed AD. Send your comments to an address listed...

  4. 76 FR 18029 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-01

    .... Model F.28 Mark 1000, 2000, 3000, and 4000 Airplanes AGENCY: Federal Aviation Administration (FAA.... Affected ADs (b) None. Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 1000, 2000... aeroplane. * * * * * Compliance (f) You are responsible for having the actions required by this AD...

  5. 75 FR 2055 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-14

    ...-16170; AD 2010-01-11] RIN 2120-AA64 Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070... February 18, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Fokker Services B.V. Model F... (f) Unless already done, do the following actions. ] (1) For airplanes equipped with booster...

  6. 76 FR 13921 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-15

    .... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION...) None. Applicability (c) This AD applies to all Fokker Services B.V. Model F.28 Mark 0070 and 0100.... * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the...

  7. 75 FR 10696 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-09

    .... Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION...) None. Applicability (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and Mark 0100...), as previously required by EASA AD 2008-0193. Compliance (f) You are responsible for having...

  8. 75 FR 47180 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-05

    ... Model 767-200, -300, and -300F Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Model 767-200...-pressure flex-hoses of the flightcrew and supernumerary oxygen system installed under the oxygen...

  9. 75 FR 8554 - Airworthiness Directives; The Boeing Company Model 747-100, -200B, and -200F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-25

    ... Model 747-100, - 200B, and -200F Series Airplanes AGENCY: Federal Aviation Administration (FAA... to supersede an existing airworthiness directive (AD) that applies to certain Model 747-100, 747-200B... upper row of fasteners holes of the skin lap joints in the fuselage lower lobe, and repair, if...

  10. 76 FR 28632 - Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-18

    ... Model 737-300, -400, and -500 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... joints at stringers S-4R and S-4L, along the entire length from body station (BS) 360 to BS 908. If a... of fasteners at stringers S-4L and S-4R. This AD was prompted by a report indicating that a Model...

  11. 75 FR 79984 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-21

    .... Model BD-100-1A10 (Challenger 300) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... 39-16297. Applicability (c) This AD applies to Bombardier, Inc. Model BD-100-1A10 (Challenger 300... of Chapter 5 of Bombardier Challenger 300 BD-100 Time Limits/Maintenance Checks. (1) For the new...

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2007-01-01

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

  14. 77 FR 64029 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Design Dive Speed

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-18

    ... with modification 160023 (Sharklet). These airplanes will have novel or unusual design features when... 160023 on Model A321 series airplanes for the installation of a ``Sharklet,'' a large wingtip device. The... 160023 (Sharklet) and later derivatives because the existing special conditions have evolved over the...

  15. 75 FR 31282 - Airworthiness Directives; Airbus Model A319-100, A320-200, A321-100, and A321-200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-03

    ...-100, A320-200, A321- 100, and A321-200 Series Airplanes AGENCY: Federal Aviation Administration (FAA... to certain Airbus Model A319-100, A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive inspections for corrosion in the inside and outside lower walls of each type A, D, E, and...

  16. 75 FR 4710 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes and A340-200, -300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-29

    ... 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; Airbus Model A330-200 and -300 Series Airplanes and A340-200, -300, -500, and -600 Series Airplanes AGENCY:...

  17. 78 FR 28159 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-14

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F...

  18. 77 FR 40485 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-10

    .... ] SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD was prompted by reports of an inoperative...

  19. 77 FR 16430 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-21

    .... SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes), and Model A310 series airplanes. This AD was prompted by a report of a crack in the...

  20. 76 FR 79558 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-22

    ...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes), and Model A310 series airplanes. This proposed AD was prompted by a report of a crack in...

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

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.; Healy, Frederick M.

    1964-01-01

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

  2. 75 FR 12464 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-11 and MD-11F Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-16

    ... Directives; McDonnell Douglas Corporation Model MD- 11 and MD-11F Airplanes AGENCY: Federal Aviation... Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846- 0001; telephone 206-544-5000.... The FAA amends Sec. 39.13 by adding the following new AD: McDonnell Douglas Corporation: Docket...

  3. 75 FR 63060 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-14

    ... INDUSTRIES S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... product. The MCAI describes the unsafe condition as: Some cases of failure of engine oil dipsticks, installed on Pratt & Whitney Canada (P&WC) PT6A66 and PT6A66B engines, were detected on P.180 aeroplanes...

  4. 75 FR 49377 - Airworthiness Directives; BAE Systems (Operations) Limited Model Avro 146-RJ and BAe 146 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-13

    ...-012-AD; Amendment 39-16387; AD 2010-16-10] RIN 2120-AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model Avro 146-RJ and BAe 146 Airplanes AGENCY: Federal Aviation Administration (FAA... has been identified regarding the interchanging of wing links on all BAe 146 & AVRO 146-RJ...

  5. 75 FR 12158 - Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model Avro 146-RJ and BAe 146 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-15

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model Avro 146-RJ and BAe 146 Airplanes AGENCY: Federal Aviation Administration (FAA... fleet wide problem has been identified regarding the interchanging of wing links on all BAe 146 &...

  6. 75 FR 52292 - Airworthiness Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-25

    ... Directives; Diamond Aircraft Industries GmbH Models DA 40 and DA 40F Airplanes AGENCY: Federal Aviation...: We propose to adopt a new airworthiness directive (AD) for all Diamond Aircraft Industries GmbH... Federal holidays. For service information identified in this proposed AD, contact Diamond...

  7. 76 FR 57627 - Special Conditions: Cessna Aircraft Company Model M680 Airplane; Rechargeable Lithium-Ion Battery...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-16

    ... Airplane; Rechargeable Lithium-Ion Battery Installations AGENCY: Federal Aviation Administration (FAA), DOT... lithium-ion batteries. The applicable airworthiness regulations do not contain adequate or appropriate... lithium-ion batteries in the Model 680. Type Certification Basis Under the provisions of Title 14, Code...

  8. 78 FR 62495 - Special Conditions: Learjet Model 35, 35A, 36, and 36A Airplanes; Rechargeable Lithium-Ion...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-22

    ... Airplanes; Rechargeable Lithium-Ion Batteries and Battery Systems AGENCY: Federal Aviation Administration... associated with rechargeable lithium-ion batteries and battery systems. These batteries have certain failure... certificate for installing equipment that uses rechargeable lithium-ion battery systems in Learjet Model...

  9. 75 FR 27959 - Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes AGENCY: Federal Aviation Administration (FAA... airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct...

  10. 75 FR 22512 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-29

    ... 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...

  11. 76 FR 54403 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-01

    ... 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,...

  12. 76 FR 10224 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-24

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

  13. 75 FR 63062 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-14

    ... 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...

  14. 77 FR 69573 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ...; Electronic Flight Control System: Lateral-Directional and Longitudinal Stability and Low Energy Awareness... airplane will have a novel or unusual design feature(s) associated with an electronic flight control system... features: (1) Lateral-Directional Static Stability: The electronic flight control system on the Model...

  15. 75 FR 2433 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-15

    ... control domain), 2. Airline business and administrative support (airline information domain), 3. Passenger information and entertainment systems (passenger entertainment domain), and 4. The capability to allow access... Administration 14 CFR Part 25 Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks...

  16. 78 FR 76251 - Special Conditions: Airbus, Model A350-900 Series Airplane; Electronic System Security Protection...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ... feature: The digital systems architecture for the Airbus Model A350-900 series airplanes is composed of several connected networks. This proposed network architecture is used for a diverse set of functions... A350-900 series architecture and network configuration may allow increased connectivity to and access...

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

    NASA Technical Reports Server (NTRS)

    MacDougall, George F., Jr.

    1947-01-01

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

  18. 75 FR 906 - Airworthiness Directives; The Boeing Company Model 747-400, -400D, and -400F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-07

    ... airplane models. Costs of Compliance This revision imposes no additional economic burden. The current costs... estimate the cost of this AD to the U.S. ] operators to be $2,288,640, or $3,840 per product. FAA's... estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for...

  19. 78 FR 31836 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Dive Speed Definition With Speed...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-28

    ..., Dive Speed Definition With Speed Protection System AGENCY: Federal Aviation Administration (FAA), DOT... design features include a high-speed protection system. The applicable airworthiness regulations do not... pilot or copilot sidestick. The Model EMB-550 airplane incorporates a high-speed protection system...

  20. 77 FR 51944 - Special Conditions: Airbus, Model A318-112 Airplane (S/N 3238); Certification of Cooktops

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-28

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A318-112 Airplane (S/N 3238); Certification of Cooktops AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...

  1. 76 FR 1351 - Airworthiness Directives; The Boeing Company Model 757-200, -200CB, and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-10

    ... Model 757-200, - 200CB, and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... exceed 30 flight cycles. Option B: At intervals not to exceed 300 flight cycles. Option C: At intervals... interval of 300 flight cycles to extend the Option B repeat inspection up to 330 flight cycles, and...

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

    NASA Technical Reports Server (NTRS)

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

    1951-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1974-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

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

  5. 78 FR 65235 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane; Crashworthiness, Emergency Landing...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ...: Mark Freisthler, FAA, Airframe/Cabin Safety, ANM-115, Transport Airplane Directorate, Aircraft.... Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING... Airplane; Crashworthiness, Emergency Landing Conditions AGENCY: Federal Aviation Administration (FAA),...

  6. 75 FR 46840 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Series Airplane; Passenger Seats With Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-04

    ...: Alan Sinclair, FAA, Airframe/Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft... Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P ... Series Airplane; Passenger Seats With Non-Traditional, Large, Non-Metallic Panels AGENCY:...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-28

    ... Gulfstream G280 Airplane; Isolation or Aircraft Electronic System Security Protection From Unauthorized... jet transport airplane with a maximum takeoff weight of 39,600 pounds and an emergency exit... support efficient design and certification of passenger cabin interiors through the supplemental...

  8. 76 FR 10528 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... will be an all-new, two- engine jet transport airplane with an executive cabin interior. The maximum... Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton... data in the aircraft control domain or airline information domain from any point within the...

  9. 77 FR 36123 - Special Conditions: Gulfstream Aerospace LP (GALP), Model Gulfstream G280 Airplane; Aircraft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-18

    ... Gulfstream G280 Airplane; Aircraft Electronic System Security Protection From Unauthorized External Access... jet transport airplane with a maximum takeoff weight of 39,600 pounds and an emergency exit... support efficient design and certification of passenger cabin interiors through the supplemental...

  10. 75 FR 61999 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

    ... airplanes. This proposed AD results from reports of fuel leaks from certain drain locations of the slat... reports of fuel leaks from certain drain locations of the slat track housing near the engine exhaust... near the engine exhaust nozzles of the wings, which could result in a fire when the airplane is...

  11. 75 FR 38945 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-07

    ... electrical systems through a switch in the flight compartment in the event of smoke or flames. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew's inability to turn... inability to control smoke or flames in the airplane flight deck or passenger cabin during a non- normal or...

  12. 76 FR 12617 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-08

    ...-essential electrical systems through a switch in the flight compartment in the event of smoke or flames. In the event of smoke or flames in the airplane flight deck or passenger cabin, the flightcrew's... result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during...

  13. 76 FR 28683 - Airworthiness Directives; Airbus Model A330 and A340 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-18

    ... proposed to revise the Airworthiness Limitations Section (ALS), for all affected airplanes, by adding new... revised ALS of the Instructions for Continued Airworthiness. Since the second supplemental NPRM was issued... Airworthiness Limitations section (ALS), for all affected airplanes, by adding new Airworthiness...

  14. 76 FR 62663 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-11

    ... structure. Continental believed the intent is to cold work the skin hole only for airplanes with titanium... working was meant for the wing skin holes for airplanes having titanium pitch load fittings. However, we have determined that the titanium fitting maintains an adequate level of safety if the cold...

  15. 75 FR 15357 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ...-to-wing upper link load path and possible separation of a strut and engine from the airplane during... possible separation of a strut and engine from the airplane during flight. Relevant Service Information We... flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and...

  16. 76 FR 73483 - Airworthiness Directives; Gulfstream Aerospace Corporation Model GV and GV-SP Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-29

    ... manual to add restrictions for APU usage for certain airplanes having a third fire extinguisher bottle..., revising the limitations section of the airplane flight manual to add restrictions for APU usage for... interest require adopting the AD as proposed--except for minor editorial changes. We have determined...

  17. 75 FR 61345 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-05

    ... requires incorporating changes to the electronic flight information system and the airplane flight manuals... electronic flight information system and the airplane flight manual. Comments We gave the public the... certain publications listed in the AD as of November 9, 2010. ADDRESSES: For service information...

  18. 76 FR 37684 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... the airplane weight and balance. This proposed AD was prompted by reports of damage around the VCS... balance. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to... compressor and associated mounting hardware. (4) Revise the airplane weight and balance. Special Flight...

  19. 76 FR 48045 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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 Airplane...

  20. 78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ... A350-900 Series Airplane; Side Stick Controller AGENCY: Federal Aviation Administration (FAA), DOT... associated with side stick controllers which require limited pilot force because they are operated by only... A350-900 series airplane is equipped with two side stick controllers instead of the conventional...

  1. 78 FR 4051 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-18

    ... series airplanes; and certain Model 757-200, -200PF, and -300 series airplanes. That AD currently...; and requires replacing the control switches of cargo doors 1 and 2 of Model 757 series airplanes. This new AD adds airplanes to the applicability and revises the initial compliance times for those...

  2. 75 FR 37991 - Airworthiness Directives; Airbus Model A330-243, -341, -342, and -343 Airplanes; and Model A340...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-01

    ... engine installed on the airplanes listed in paragraph (g)(1) of this AD, having serial number 964 and... person may install a Rolls-Royce Trent 500 or Trent 700 series engine on any airplane, unless it is in... series engines.'' Airplanes with engines other than Rolls- Royce Trent 500 and Trent 700 are not affected...

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

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1996-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Bryant, Robert L.

    1948-01-01

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

  7. Airplane Ear

    MedlinePlus

    ... severe hearing loss Ringing in your ear (tinnitus) Spinning sensation (vertigo) Vomiting resulting from vertigo Bleeding from ... the back of the nasal cavity and the top of the throat meet (nasopharynx). When an airplane ...

  8. Giant airplanes

    NASA Technical Reports Server (NTRS)

    Warner, Edward P

    1922-01-01

    It is hardly possible for the most imaginative aeronautical enthusiast to look forward to a time when the airplane will have reached the dimensions commensurate with those already attained by the airship.

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

    NASA Technical Reports Server (NTRS)

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

    1947-01-01

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

  10. Flight Tests of A 1/8-Scale Model of the Bell D-188A Jet VTOL Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1959-01-01

    The Bell D-188A VTOL airplane is a horizontal-attitude VTOL fighter with tilting engine nacelles at the tips of a low-aspect-ratio unswept wing and additional engines in the fuselage. The model could be flown smoothly in hovering and transition flight. In forward flight the model could be flown smoothly at the lower angles of attack but experienced an uncontrollable directional divergence at angles of attack above about 16 deg.

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

    NASA Technical Reports Server (NTRS)

    Cumming, Stephen B.; Diebler, Corey G.

    2005-01-01

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

  12. 76 FR 63818 - Special Conditions: Boeing Model 767-400ER Series Airplanes; Seats With Inflatable Lapbelts

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-14

    ... Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind...- 400ER series airplane. These airplanes, as modified by Continental Airlines, will have a novel or... Continental Airlines 767-400ER series airplane. Should Continental Airlines apply at a later date for...

  13. Gottingen six-component scale measurements on a Junkers A 35 airplane model

    NASA Technical Reports Server (NTRS)

    Blenk, Hermann

    1930-01-01

    The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes.

  14. 76 FR 36863 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Protection From...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ... configuration may allow the exploitation of network security vulnerabilities resulting in intentional or...; Electronic Systems Security Protection From Unauthorized External Access AGENCY: Federal Aviation... architecture and connectivity capabilities of the airplane's computer systems and networks, which may...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-18

    ... Administration, Small Airplane Directorate, Aircraft Certification Service, 901 Locust, Room 301, Kansas City, MO... aircraft. It incorporates an Electronic Flight Information System (EFIS), pressurized cabin, retractable... incorporate sophisticated equipment not previously used in a part 23 aircraft. Additionally, part 23...

  16. 75 FR 81430 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ... airplanes, an inspection for steel cross-shaped doublers on the larger aluminum doublers; and corrective... inspection for steel cross- shaped doublers on the larger aluminum doublers; and corrective action if...

  17. 78 FR 65155 - Special Conditions: Learjet Model 45 Series Airplanes; Isolation or Security Protection of the...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... information domain); and 3. Passenger information and entertainment systems (passenger entertainment domain... interconnected networks and systems, such as passenger entertainment and information services than previous... associated with connectivity of the passenger service computer systems to the airplane critical systems and...

  18. 76 FR 15818 - Airworthiness Directives; Reims Aviation S.A. Model F406 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  19. 75 FR 32263 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... airplanes, certificated in any category, serial numbers 4105 through 4179 inclusive. Subject (d) Air... having serial numbers 4113 through 4179 inclusive: Within 750 flight hours after the effective date...

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

    NASA Technical Reports Server (NTRS)

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

    1959-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2001-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; McBride, Ellis E.

    1948-01-01

    Tests were made of a 1/10-scale dynamically similar model of the North American XFJ-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording the accelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history acceleration curves. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down landing attitude of 12 deg. The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned if any appreciable load of fuel remains; if empty, they should be retained for additional buoyancy. In a calm-water ditching the airplane will probably run about 600 feet Maximum longitudinal decelerations of about 2.5g and maximum vertical acceleration of about 2g will be encountered. The nose-intake duct will be clear of the water until practically all forward motion has stopped.

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

    NASA Technical Reports Server (NTRS)

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

    1974-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Pepper, Edward; Foster, Gerald V.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Hoffman, Edward L.; Fisher, Lloyd J.

    1950-01-01

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

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

    NASA Astrophysics Data System (ADS)

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

    1981-12-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1984-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1981-01-01

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

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

    PubMed

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

    2014-01-01

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

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

    PubMed Central

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

    2014-01-01

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

  11. Free-Spinning-Tunnel Tests of a 1/20-Scale Model of the Northrop N-9M Airplane

    NASA Technical Reports Server (NTRS)

    MacDougall, George F., Jr.; Lichtenstein, Jacob H.

    1946-01-01

    Spin tests of a 1/20-scale model of the Northrop N-9M airplane have been performed in the Langley 20-foot free-spinning tunnel. The erect and inverted spin and recovery characteristics were determined for various loading conditions and the effect of deflecting the flaps and of extending the landing gear was investigated. The investigation also included tests to determine the size parachute required for satisfactory spin recovery by parachute action alone. The tests were performed at an equivalent spin altitude of 15,000 feet. A specialized recovery technique consisting of rapid full reversal of the rudder pedals against the spin combined with turning the wheel against the spin and movement of the stick forward is recommended for all loadings and configurations of the airplane. The results also indicated that a 7-foot-diameter spin-recovery parachute having a drag coefficient of 0.7 attached to the outboard wing tip with a towline of 10 to 30 feet or an 8.8-foot-diameter parachute attached to the fixed portion of the wing between the elevons and the pitch flaps with a 30-foot towline would provide satisfactory recovery from demonstration spins by parachute action alone. It appears possible that the first N-9M airplane may have crashed because of failure to recover from a spin.

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

    NASA Technical Reports Server (NTRS)

    Brewer, Gerald W.

    1946-01-01

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

  13. 78 FR 78285 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-26

    ...We propose to supersede airworthiness directive (AD) 2005-23- 08 that applies to certain Airbus Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23-08 required repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and......

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

    NASA Technical Reports Server (NTRS)

    Jarvis, George A.; Fisher, Lloyd J.

    1946-01-01

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

  15. 77 FR 67267 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-09

    ... rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional...

  16. 77 FR 40826 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-11

    ...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet...

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

    NASA Technical Reports Server (NTRS)

    Jarvis, George A.; Cederborg, Gibson A.

    1946-01-01

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

  18. 75 FR 36577 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-28

    ...-30 airplanes. The existing AD currently requires modifying the auxiliary hydraulic power system... AD requires modifying the auxiliary hydraulic power system (including doing all applicable related... Code 29: Hydraulic Power. Unsafe Condition (e) This AD results from fuel system reviews conducted by...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-08

    ... proposed AD would require inspecting for cracks and corrosion of the bracket of the inboard horizontal... applicability to remove certain airplanes. This proposed AD results from a report of cracking and corrosion... AD to prevent such cracking and corrosion of the elevator inboard-hinge brackets and the...

  20. 76 FR 69685 - Airworthiness Directives; The Boeing Company Model 767-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-09

    ... Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207... INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this... information describes procedures for repetitive detailed inspections or surface high frequency eddy...

  1. 76 FR 65938 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-25

    ... the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12... the compliance times specified, unless the actions have already been done. Resistance Measurement (g.... 02 September 3, 2007. (1) For configuration 05 airplanes: Do a resistance check of the inboard...

  2. 76 FR 54141 - Airworthiness Directives; Cessna Aircraft Company Model 680 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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 and...

  3. 76 FR 27220 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-11

    ... structural integrity of the wings. We are issuing this AD to require actions to correct the unsafe condition... (SBs which address structure fatigue related areas on the wing parts), until now part of the... wings. The required corrective actions are as follows, depending on airplane configuration: For...

  4. 76 FR 5503 - Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-01

    ... the event of smoke or flames. The flightcrew's inability to turn off electrical power to the IFE system and other non-essential electrical systems in the event of smoke or flames could result in the inability to control smoke or flames in the airplane flight deck or passenger cabin during a non-normal or...

  5. 78 FR 65153 - Special Conditions: Learjet Model 45 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... design feature associated with the architecture and connectivity capabilities of the airplanes' computer..., data, or views. The most helpful comments reference a specific portion of the special conditions, explain the reason for any recommended change, and include supporting data. We will consider all comments...

  6. 75 FR 6092 - Special Conditions: Model C-27J Airplane; Class E Cargo Compartment Lavatory

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-08

    ... or unusual design features when compared to the state of technology described in the airworthiness standards for transport-category airplanes. These design features include a lavatory in the Class E cargo... for these design features. These special conditions contain the additional safety standards that...

  7. 75 FR 50867 - Airworthiness Directives; Airbus Model A330-223, -321, -322, and -323 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-18

    ...-223, -321, -322, and -323 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... (PW) forward (FWD) engine mount pylon bolts. * * * * * Dual-bolt fractures could lead to inability for mount assembly to sustain loads which may lead to an engine mount failure and consequently to engine...

  8. 75 FR 34349 - Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. Various Models MU-2B Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-17

    ... airplanes. An FAA MU-2B safety evaluation resulted in the standardization of the MU-2B specific training and... evaluation had no regulatory basis and were locally produced. This resulted in a lack of standardization for... standardization for critical operating procedures in training and in the FAA-accepted pilot operating checklists...

  9. 75 FR 50854 - Airworthiness Directives; The Boeing Company Model 767-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-08-18

    ...; e-mail me.boecom@boeing.com ; Internet https://www.myboeingfleet.com . Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov ; or in person at the Docket... several large transport airplanes, including the adequacy of existing regulations, the service history of...

  10. 75 FR 38056 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-01

    ..., which could lead to separation of the support fittings from the pylon, and could result in separation of... fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane. Actions Since Existing AD Was Issued The preamble to AD 2008-18...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-09

    ... require incorporating changes to the electronic flight information system and the airplane flight manuals... AD would require you to incorporate changes to the electronic flight information system and the... 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this...

  12. 75 FR 80742 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-23

    ... MD-90-30 airplanes. This proposed AD would require repetitive inspections for cracking of the left.... This proposed AD was prompted by a report of a crack found in the upper skin panel at the aft inboard corner of a right horizontal stabilizer. We are proposing this AD to detect and correct cracks in...

  13. 76 FR 3054 - Airworthiness Directives; The Boeing Company Model 777 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-19

    ... to detect fatigue cracking of principal structural elements (PSEs). This proposed AD was prompted by... proposing this AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes. DATES: We must...

  14. 75 FR 53843 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-02

    ... certain fuselage frames and stub beams, and corrective actions if necessary. For certain airplanes, this... requires a modification which includes reinforcing the body frame inner chords, replacing the stub beam upper chords and attach angles, and reinforcing the stub beam web. This AD results from reports of...

  15. 75 FR 81417 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ...) backup battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight..., 2010 (75 FR 61655). That NPRM proposed to require installation of a FADEC backup battery, replacement.... Action Labor cost Parts cost product operators Installation of a FADEC backup battery 7 work-hours x...

  16. 75 FR 78177 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-15

    ... battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and replacing the FADEC backup battery every 12 calendar months. This proposed AD was prompted by an incident... allow the FADEC to shut down or reset if the main battery is depleted and the electrical charging system...

  17. 75 FR 81422 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ... bundles, causing shorts in many systems, including the spar fuel shut-off valve, oxygen mask deployment... extremely remote, and disagrees with the references to the spar shut-off valve, oxygen masks, and... engine. In regard to the airplane's oxygen system, while failure of the oxygen mask deployment...

  18. 75 FR 22503 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-29

    ... the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2010-05, dated... information as follows: (1) Canadian Airworthiness Directive CF-2010-05, dated February 2, 2010, requires an.... (2) Canadian Airworthiness Directive CF-2010-05, dated February 2, 2010, states that an airplane may...

  19. 76 FR 81360 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G280 Airplane, Operation Without Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-28

    ... generation and distribution architecture is equipped with an auxiliary power unit (APU) and is not equipped... requires a continuous source of electrical power for continued safe flight and landing. The current..., it must be demonstrated that the airplane can continue through safe flight and landing...

  20. 76 FR 8607 - Airworthiness Directives; The Cessna Aircraft Company Model 750 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    ... requires an inspection to determine the serial numbers of the auxiliary power unit (APU) generator and the left and right engine direct current (DC) generators, and corrective actions if necessary. This AD also requires revising the airplane flight manual. This AD was prompted by a report of a DC...

  1. 75 FR 68731 - Airworthiness Directives; The Cessna Aircraft Company Model 750 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-09

    ... the serial numbers of the auxiliary power unit (APU) generator and the left and right engine direct current (DC) generators, and related corrective actions if necessary. This proposed AD would also require revising the airplane flight manual. This proposed AD results from a report of a DC generator...

  2. 75 FR 70863 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-19

    ... structure, as applicable. We are proposing this supplemental NPRM to prevent electrical current from flowing... the electrical bond resistance between the motor operated valve (MOV) actuators and airplane structure... proposed to require measuring the electrical bond resistance between the motor operated valve...

  3. 75 FR 60665 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-01

    ... MD-90-30 airplanes. This proposed AD would require repetitive high frequency eddy current inspections... 17, 2010, describes procedures for doing repetitive high frequency eddy current (HFEC) inspections... this AD, do a high frequency eddy current (HFEC) inspection for cracking on the hinge bearing lugs...

  4. 76 FR 18038 - Airworthiness Directives; Airbus Model A340-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-01

    ...-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... condition on an aviation product. The MCAI describes the unsafe condition as: Two A340-300 aeroplanes... ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Two...

  5. 75 FR 61655 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-06

    ... battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and.... ADDRESSES: Use one of the following addresses to comment on this proposed AD: Federal eRulemaking Portal: Go... can allow the FADEC to shut down or reset if the main battery is depleted and the electrical...

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

    NASA Technical Reports Server (NTRS)

    Hartman, Edwin P

    1938-01-01

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

  7. 76 FR 26957 - Special Conditions: Boeing, Model 747-8 Series Airplanes; Door 1 Extendable Length Escape Slide

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-10

    ...: Jayson Claar, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft... four-engine jet transport airplane that will have a maximum takeoff weight of 975,000 pounds, new.... Whenever passengers are carried on the main deck of the airplane, there must be a cabin...

  8. 75 FR 35 - Special Conditions: Airbus Model A318-112 Airplane (S/N 3886); Certification of a Cooktop

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ... Electrical Equipment,'' and those in AC 25-17, ``Transport Airplane Cabin Interiors Crashworthiness Handbook... Branch, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton... possibility of fire into the passenger-cabin environment. These potential hazards to the airplane and...

  9. 78 FR 11556 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ... INFORMATION CONTACT: Todd Martin, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane... is the first of a new family of jet airplanes designed for corporate flight, fractional, charter, and... Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P...

  10. 76 FR 26949 - Special Conditions: Boeing Model 747-8 Series Airplanes; Overhead Flight Attendant Rest Compartment

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-10

    ..., Transport Standards Staff, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue...-engine jet transport airplane that will have a maximum takeoff weight of 975,000 pounds and new General... airplane. Crew rest compartments have been installed and certified in the main passenger cabin area...

  11. 78 FR 26280 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-06

    ...: Jayson Claar, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft... first of a new family of jet airplanes designed for corporate flight, fractional, charter, and private... EMB-550 airplane has proposed interior configurations that include multiple-place side-facing...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-29

    ... charts in the FAA-approved airplane flight manual and the pilot's operating handbook, part number (P/N... published data in the airplane flight manual and the pilot's operating handbook and ensure it corresponds... Corporation Temporary Change to the Pilot's Operating Handbook and FAA-Approved Airplane Flight Manual, P/N...

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Tarshis, Robert P.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1960-01-01

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

  15. 78 FR 46532 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-01

    ... occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed... directive (AD) for all The Boeing Company Model 767 airplanes. That NPRM proposed to require repetitive.... That NPRM was prompted by reports of two in-service occurrences on Model 737-400 airplanes of...

  16. 77 FR 16490 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-21

    ...). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This proposed AD was prompted...

  17. 75 FR 35356 - Airworthiness Directives; The Boeing Company Model 747-100, 747-200B, and 747-200F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-22

    ..., corrosion, and bulging of the skin lap joints on Boeing Model 747-100, 747-200B, and 747-200F series... Model 747-100, 747- 200B, and 747-200F Series Airplanes AGENCY: Federal Aviation Administration (FAA... to supersede two existing airworthiness directives (AD) that apply to certain Model 747-100,...

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

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1972-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1964-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1964-01-01

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

  2. Reduction of vertical-gust induced loads on elastic airplane model with slotted-interceptor-type surfaces

    NASA Astrophysics Data System (ADS)

    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.

  3. Load Analysis and Critical Area Stress Analysis of the 126-AR00036 and 126-AR00037 Parachute Testers when Installed on the F-4C/D Aircraft Centerline Station

    DTIC Science & Technology

    1976-11-01

    11»»!1 LOAD ANALYSIS AND CRITICAL AREA STRESS ANALYSIS OF THE 126-AR00036 AND 126-AR00037 PARACHUTE TESTERS WHEN INSTALLED ON THE F-4C/D...LOAD ANALYSIS AND CRITICAL AREA STRESS ANALYSIS OF/ TOE f26’A|*0OÖ36 AND 126-AB0ÖO37 PARACHUTE JESTERS / WHEN INSmLED ON THE f-^/D AIRCRAFT CENTERLINE...Analysis if ABSTRACT (Continue on reverse aide II necestary and Identlly by block number) This report documents the loads and critical stress

  4. 77 FR 16661 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-22

    ... Model A330-200 and -300 series airplanes, and Model A340- 200, -300, -500, and -600 series airplanes... the pitot probes, which could lead to an air leak, resulting in incorrect total pressure measurement..., August 18, 2010). That AD required actions intended to address an unsafe condition on certain Model...

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

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.; Berman, Theodore

    1948-01-01

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

  6. 78 FR 41882 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-12

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault Aviation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM... Aviation Model Falcon 2000 series airplanes. That AD currently requires repetitive operational...

  7. 77 FR 54846 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-06

    ...-1A10 (Challenger 300) airplanes. This proposed AD was prompted by reports of failure of a screw cap or... Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated in any category, having serial...

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

    NASA Technical Reports Server (NTRS)

    Campbell, John P; Seacord, Charles L , Jr

    1943-01-01

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

  9. Investigation of the Trim Characteristics of a 1/20-Scale Model of the Fleetwings XBTK-1 Airplane over a Wide Range of Angles of Attack

    NASA Technical Reports Server (NTRS)

    Stone, Ralph W., Jr.; Berman, Theodore

    1947-01-01

    Tests of a 1/20-scale model of the Fleetwings XBTK-1 airplane have been performed in the Langley 15-foot free-spinning tunnel to determine the trim tendencies of the airplane at attitudes above the stall. The results of the tests indicated that the model would trim longitudinally only in the normal range of angles of attack and that the yaw trim tendencies for such longitudinal trim conditions were normal. Although wide oscillations in yaw were noted for some conditions, they occurred at angles of attack larger than those indicated as possible for longitudinal trim and spin equilibrium. It appears, therefore, that the oscillatory motions reported for the airplane may have been the direct result of control movements rather than the result of inherent oscillatory tendencies.

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Thompson, William C.

    1955-01-01

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

  11. Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF1OF-1 Airplane

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1950-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made. The results indicated that in the straight-wing configuration, satisfactory recoveries of the airplane will be obtained from erect and inverted spins by rudder reversal alone. In the swept-wing configuration recoveries will be unsatisfactory from erect spins. Unsweeping the wings during the spin and reversal of the rudder, however, will lead to eventual recovery. The test results also indicated that, if existing small ailerons are made deflectable through large angles, satisfactory recoveries will be obtained from erect spins in the swept-wing configuration by simultaneous movement of the rudder to against the spin and movement of the ailerons to with the spin. Normal-size ailerons deflected through a normal range would also be effective. Satisfactory recoveries by rudder reversal will be obtained from inverted spins in the swept-wing configuration. In the straight-wing configuration a 14.2-foot tail parachute or a 5.0-foot wing-tip parachute opened on the outer wing tip will effect satisfactory recovery of the airplane by parachute action alone; a 30.0-foot tail parachute or a 10.0-foot wing-tip parachute will be required for the swept-wing configuration. The forces required to fully reverse the rudder should be within the capabilities of the pilot.

  12. 77 FR 23420 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-19

    ... Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently... have determined that, for certain airplanes, reducing the compliance time for a certain replacement is... on certain Bombardier, Inc. Model CL-600- 2B19 (Regional Jet Series 100 & 440) Airplanes. Since we...

  13. 77 FR 75911 - Airworthiness Directives; Embraer S.A. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-26

    ... S.A. Model ERJ 170 and ERJ 190 airplanes. The existing AD currently requires, for certain airplanes... bleed system with a new check valve and new seals, replacing the low pressure check valves (LPCV), and... received reports of uncommanded engine shutdowns on both Model ERJ 170 and ERJ 190 airplanes due...

  14. 78 FR 38550 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-27

    ... new airworthiness directive (AD) for all The Boeing Company Model 747SP series airplanes, and certain The Boeing Company Model 747-100B SUD and 747-300 series airplanes. This AD was prompted by an... integrity of the airplane and sudden loss of cabin pressure. DATES: This AD is effective August 1, 2013....

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

    NASA Technical Reports Server (NTRS)

    White, Richard P.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1956-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Thompson, William C.

    1949-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Paulson, John W.; Johnson, Joseph L.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1992-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Yip, Long P.

    1987-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1973-01-01

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

  2. Wind tunnel test of model target thrust reversers for the Pratt and Whitney aircraft JT8D-100 series engines installed on a 727-200 airplane

    NASA Technical Reports Server (NTRS)

    Hambly, D.

    1974-01-01

    The results of a low speed wind tunnel test of 0.046 scale model target thrust reversers installed on a 727-200 model airplane are presented. The full airplane model was mounted on a force balance, except for the nacelles and thrust reversers, which were independently mounted and isolated from it. The installation had the capability of simulating the inlet airflows and of supplying the correct proportions of primary and secondary air to the nozzles. The objectives of the test were to assess the compatibility of the thrust reversers target door design with the engine and airplane. The following measurements were made: hot gas ingestion at the nacelle inlets; model lift, drag, and pitching moment; hot gas impingement on the airplane structure; and qualitative assessment of the rudder effectiveness. The major parameters controlling hot gas ingestion were found to be thrust reverser orientation, engine power setting, and the lip height of the bottom thrust reverser doors on the side nacelles. The thrust reversers tended to increase the model lift, decrease the drag, and decrease the pitching moment.

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

    NASA Technical Reports Server (NTRS)

    McKee, John W.; Vogler, Raymond D.

    1947-01-01

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

  4. Airplane Balance

    NASA Technical Reports Server (NTRS)

    Huguet, L

    1921-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Murch, Austin M.; Foster, John V.

    2007-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.; Lee, Henry A.

    1954-01-01

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

  7. 78 FR 78292 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-26

    ... Aviation Model FALCON 7X airplanes. AD 2011-13-07 requires revising the airplane flight manual (AFM) to..., Dassault Aviation developed an Airplane Flight Manual (AFM) operational procedure that, in case of RA 1... has been deleted. Finally, many editorial changes have been made to align the writing of the AD...

  8. 77 FR 21429 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-10

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was... these airplanes. DATES: This AD is effective May 15, 2012. The Director of the Federal Register...

  9. 77 FR 13193 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-06

    .... Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION..., and -106 airplanes and Model DHC-8-200, -300, and -400 series airplanes. This AD was prompted...

  10. 76 FR 69161 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-08

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION.... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM... (Regional Jet Series 700, 701, & 702) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes;...

  11. 76 FR 71470 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-18

    ...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of...-102, -103, and -106 airplanes and Model DHC-8-200, -300, and -400 series airplanes. This proposed...

  12. 77 FR 6525 - Airworthiness Directives; Bombardier, Inc., Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-08

    ... directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. That NPRM proposed...-1A10 (Challenger 300) airplanes. Since that NPRM (76 FR 64857, October 19, 2011) was issued, we have... BD-100-1A10 (Challenger 300) airplanes, this AD applies to serial numbers 20003 and subsequent. This...

  13. 76 FR 17582 - Special Conditions: Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes, Head-Up Display (HUD...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-30

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes, Head-Up Display (HUD) With Video Synthetic Vision System (SVS) AGENCY: Federal...

  14. 78 FR 75511 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-12

    ... Inc., Models BD-500-1A10 and BD- 500-1A11 Series Airplanes; Electronic Flight Control System: Control... control system. The applicable airworthiness regulations do not contain adequate or appropriate safety... control system (EFCS) and no direct coupling from the flightdeck controller to the control surface. As...

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

    NASA Technical Reports Server (NTRS)

    Hunton, Lynn W.; Dew, Joseph K.

    1949-01-01

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

  16. 75 FR 43397 - Airworthiness Directives; Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-26

    ...-067-AD; Amendment 39-16338; AD 2010-13-07] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc... in the Federal Register on June 23, 2010 (75 FR 35619), and applies to certain Piper Aircraft, Inc... certain Piper Aircraft, Inc. Models PA-32R-301T and PA-46-350P airplanes. AD 2010-13-07 requires you to...

  17. 75 FR 3125 - Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-20

    ...-16152; AD 2009-26-13] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200, A330-300, A340- 200,and A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... 1, 2009. Manual. Airbus A340-200/-300 Structural 64 October 1, 2008. Repair Manual. Airbus...

  18. 77 FR 69568 - Special Conditions: Bombardier Aerospace, Model BD-500-1A10 and BD-500-1A11 Airplanes; Sidestick...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ... Aerospace, Model BD-500-1A10 and BD-500-1A11 Airplanes; Sidestick Controllers AGENCY: Federal Aviation... have a novel or unusual design feature, specifically sidestick controllers designed to be operated with... sidestick controller instead of a conventional control column and wheel. This kind of controller is designed...

  19. Ditching Investigation of a 1/12-Scale Model of the Douglas F4D-1 Airplane, TED No. NACA DE 384

    NASA Technical Reports Server (NTRS)

    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.

  20. Effect of human movement on airborne disease transmission in an airplane cabin: study using numerical modeling and quantitative risk analysis.

    PubMed

    Han, Zhuyang; To, Gin Nam Sze; Fu, Sau Chung; Chao, Christopher Yu-Hang; Weng, Wenguo; Huang, Quanyi

    2014-08-06

    Airborne transmission of respiratory infectious disease in indoor environment (e.g. airplane cabin, conference room, hospital, isolated room and inpatient ward) may cause outbreaks of infectious diseases, which may lead to many infection cases and significantly influences on the public health. This issue has received more and more attentions from academics. This work investigates the influence of human movement on the airborne transmission of respiratory infectious diseases in an airplane cabin by using an accurate human model in numerical simulation and comparing the influences of different human movement behaviors on disease transmission. The Eulerian-Lagrangian approach is adopted to simulate the dispersion and deposition of the expiratory aerosols. The dose-response model is used to assess the infection risks of the occupants. The likelihood analysis is performed as a hypothesis test on the input parameters and different human movement pattern assumptions. An in-flight SARS outbreak case is used for investigation. A moving person with different moving speeds is simulated to represent the movement behaviors. A digital human model was used to represent the detailed profile of the occupants, which was obtained by scanning a real thermal manikin using the 3D laser scanning system. The analysis results indicate that human movement can strengthen the downward transport of the aerosols, significantly reduce the overall deposition and removal rate of the suspended aerosols and increase the average infection risk in the cabin. The likelihood estimation result shows that the risk assessment results better fit the outcome of the outbreak case when the movements of the seated passengers are considered. The intake fraction of the moving person is significantly higher than most of the seated passengers. The infection risk distribution in the airplane cabin highly depends on the movement behaviors of the passengers and the index patient. The walking activities of the crew

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

    NASA Technical Reports Server (NTRS)

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

    1975-01-01

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

  2. Optimal back-to-front airplane boarding.

    PubMed

    Bachmat, Eitan; Khachaturov, Vassilii; Kuperman, Ran

    2013-06-01

    The problem of finding an optimal back-to-front airplane boarding policy is explored, using a mathematical model that is related to the 1+1 polynuclear growth model with concave boundary conditions and to causal sets in gravity. We study all airplane configurations and boarding group sizes. Optimal boarding policies for various airplane configurations are presented. Detailed calculations are provided along with simulations that support the main conclusions of the theory. We show that the effectiveness of back-to-front policies undergoes a phase transition when passing from lightly congested airplanes to heavily congested airplanes. The phase transition also affects the nature of the optimal or near-optimal policies. Under what we consider to be realistic conditions, optimal back-to-front policies lead to a modest 8-12% improvement in boarding time over random (no policy) boarding, using two boarding groups. Having more than two groups is not effective.

  3. 78 FR 65156 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ...: Mark Freisthler, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate... E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING... BD- 500-1A11 Series Airplanes; Interactions of Systems and Structures AGENCY: Federal...

  4. 75 FR 9756 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-100 and DHC-8-200 Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-04

    ..., and -315 airplanes. This AD requires implementing a corrosion prevention and control program (CPCP... indications of corrosion. We are issuing this AD to prevent structural failure of the airplane due to corrosion. DATES: This AD is effective April 8, 2010. The Director of the Federal Register approved...

  5. 75 FR 37 - Special Conditions: Airbus Model A330 Series Airplanes; Seats with Non-Traditional, Large, Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ..., Airframe/Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601... required of large, non-metallic panels in the cabin interior. At the time the applicable rules were written... in cabins of airplanes that otherwise are not required to meet these standards. Should Airbus...

  6. 77 FR 57481 - Special Conditions: Embraer S.A., Models EMB-135 and EMB-145 Series; Airplane Seats with Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-18

    ... Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue... standards required of large, non-metallic panels in the cabin interior. At the time the applicable rules... in these special conditions. Previously certificated interiors on the existing airplane fleet...

  7. 76 FR 17334 - Special Conditions: Boeing Model 747-2G4B Airplane; Certification of Cooktops

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-29

    ... modification is limited to removing the existing cooktops and replacing them with new technology cooktops. No... airplane. This airplane, as modified by Greenpoint Technologies, Inc., will have a novel or unusual design feature associated with the replacement and re-certification of existing cooktops with advanced technology...

  8. 75 FR 15322 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... UPS, asks that all cargo-only airplanes currently in operation be exempt from the NPRM requirements.... UPS notes that changing the maintenance programs to add bonding checks will be sufficient to address the HSP issue in the existing cargo-only airplanes. UPS states that it does not object to new cargo...

  9. 75 FR 64633 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-20

    ... structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane... structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane... Paragraph in the AD We have added a new paragraph (d) to this AD to provide the Air Transport Association...

  10. 76 FR 22305 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-21

    ...) electronics units in certain power management panels; installing airplane information management system 2...) electronics units in certain power management panels; installing airplane information management system 2..., and installing power control circuitry for the center override/jettison and main jettison fuel...

  11. 76 FR 47427 - Airworthiness Directives; The Boeing Company Model 747-400 and -400F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-05

    ...) drip shields, and repairs if necessary; installation of a fiberglass reinforcing overcoat; and, for certain airplanes, installation of stiffening panels to the MEC drip shields. This AD was prompted by a... airplane was on the ground, and multiple operator reports of cracked ] MEC drip shields. We are issuing...

  12. 75 FR 30284 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-01

    ... scale fatigue test, cracks were found in some structural components of the airplane. Analysis of these... detection of fatigue cracks. Undetected fatigue cracks in these areas could adversely affect the structural.... The MCAI states: During ERJ 170 airplane full scale fatigue test, cracks were found in some...

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

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1948-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Kelly, Mark W.; Smaus, Louis H.

    1952-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Silvers, H. Norman; Spreemann, Kenneth P.

    1947-01-01

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

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

    NASA Astrophysics Data System (ADS)

    Sato, Osamu; Kobayashi, Osamu

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

  17. Stability of airplanes

    NASA Technical Reports Server (NTRS)

    Warner, Edward P

    1922-01-01

    The author attempts to correct the misconception that piloting an airplane requires extraordinary skill and balance. He also tries to show that airplanes are extremely stable in flight. Some of the major points covered in this article include: automatic pilots, airplanes designed to be stable, and the reliance on mathematics to help in designing stable aircraft.

  18. 77 FR 50644 - Airworthiness Directives; Cessna Airplane Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-22

    ... inspection of the number of hours on the A/C compressor hour meter, inspection of the logbook, and... compressor hour meter on Cessna Model 525 airplanes that have P/N 1134104-1 or 1134104-5 A/C compressor motor... following: (1) Inspect the number of hours on the A/C compressor hour meter; and (2) Check the...

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

    NASA Technical Reports Server (NTRS)

    Holleman, E. C.

    1976-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Holleman, E. C. (Compiler)

    1974-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Hoffman, Edward L.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Ralston, J.

    1983-01-01

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

  3. The 727 airplane side inlet low-speed performance confirmation model test for refanned JT8D engines

    NASA Technical Reports Server (NTRS)

    Schuehle, A. L.

    1974-01-01

    The results of a low-speed wind tunnel test of a 0.3 scale model 727 airplane side inlet for JT8D-100 engines are presented. The objectives of the test were to develop lines for a full-scale flightworthy inlet, to evaluate inlet total pressure recovery and steady-state total pressure distortion, and to obtain model-scale distortion data which can be used in the assessment of the compatibility of the inlet with the JT8D-100 series engines. A secondary objective was to obtain internal/external cowl static pressures for the determination of nacelle loads. Two basic inlet models were tested at static, forward speed, angle-of-attack (inflow angle), and cross-wind conditions. One model was with and one without an acoustic ring. Two modifications to the models were also tested, one with the ring closer to the inlet throat and one with a larger lip. Test measurements consisted of inlet surface static pressure, engine face total pressure, inlet airflow, tunnel total pressure, tunnel total temperature and tunnel velocity. Total pressure traverses were taken directly behind the ring and strut. No dynamic measurements were taken.

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

    NASA Technical Reports Server (NTRS)

    Axelson, John A.; Emerson, Horace F.

    1949-01-01

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

  5. 77 FR 10691 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    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...

  6. Testing a Windmill Airplane ("autogiro")

    NASA Technical Reports Server (NTRS)

    Seiferth, R

    1927-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.

    1956-01-01

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

  8. Theoretical computation of thermophysical properties of high-temperature F2, CF4, C2F2, C2F4, C2F6, C3F6 and C3F8 plasmas

    NASA Astrophysics Data System (ADS)

    Wang, WeiZong; Wu, Yi; Rong, MingZhe; Éhn, László; Černušák, Ivan

    2012-07-01

    The calculated values of thermodynamic and transport properties of pure F2 and fluorocarbon compounds CF4, C2F2, C2F4, C2F6, C3F6 and C3F8 at high temperatures are presented in this paper. The thermodynamic properties are determined by the method of Gibbs free energy minimization, using standard thermodynamic tables. The transport properties, including electron diffusion coefficients, viscosity, thermal conductivity and electrical conductivity, are evaluated using the Chapman-Enskog method expanded up to the third-order approximation (second order for viscosity). The most accurate cross-section data that could be located are used to evaluate collision integrals. The calculations based on the assumption of local thermodynamic equilibrium are performed for atmospheric-pressure plasmas in the temperature range from 300 to 30 000 K for different pressures between 0.1 and 10 atm. The results of F2, CF4, C2F2, C2F4 and C2F6 are compared with those of previously published studies. Larger discrepancies occur for transport coefficients; these are explained in terms of the different values of the collision integrals that were used. The results presented here are expected to be more accurate because of the improved collision integrals employed.

  9. 75 FR 1527 - Special Conditions: Bombardier, Inc., Model DHC-8-100, -200, -300, and -400 Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-12

    ...: Michael Menkin, FAA, Standardization Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-22793 facsimile... Directorate, Aircraft Certification Service. BILLING CODE 4910-13-P ...

  10. 78 FR 68985 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-18

    ... support (operator information services), 3. Passenger information systems, and, 4. Access by systems... will have more interconnected networks and systems, such as passenger entertainment and information... and connectivity of the passenger service computer network systems to the airplane critical systems...

  11. 76 FR 40286 - Airworthiness Directives; Empresa Brasileira de Aeronáutica S.A. (EMBRAER) Model EMB-505 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-08

    ... receipt. FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane... requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford,...

  12. 76 FR 444 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ... INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301... the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace...

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

    NASA Technical Reports Server (NTRS)

    Snyder, Thomas L.

    1948-01-01

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

  14. Supplementary Free-Spinning-Tunnel Tests of a 1/16-Scale Model of the McDonnell XB-85 Airplane Equipped with a Conventional-Tail Arrangement

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.

    1947-01-01

    Spin tests have been conducted in the Langley free-spinning tunnel on a 1/16-scale model of the McDonnell XP-85 airplane with the normal X-tail replaced with a short-coupled conventional tail arrangement. The effect of the conventional tail arrangement and the effects of various modifications upon the spin and recovery characteristics of the model were determined. The results of the tests indicated that installation of the conventional tail arrangement wil not provide satisfactory recoveries from spins of the airplane. Satisfactory recoveries will be obtainable, however, either by installing in addition a very large ventral fin (17.94 sq ft, full-scale) below the tail or by decreasing the width of the fuselage and making it flat sided rearward of the wing trailing edge.

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

    NASA Technical Reports Server (NTRS)

    Murphy, A. C.

    1981-01-01

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

  16. Vertical Descent and Landing Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Still Air, TED No. NACA DE 368

    NASA Technical Reports Server (NTRS)

    Smith, Charlee C., Jr.; Lovell, Powell M., Jr.

    1954-01-01

    An investigation is being conducted to determine the dynamic stability and control characteristics of a 0.13-scale flying model of Convair XFY-1 vertically rising airplane. This paper presents the results of flight and force tests to determine the stability and control characteristics of the model in vertical descent and landings in still air. The tests indicated that landings, including vertical descent from altitudes representing up to 400 feet for the full-scale airplane and at rates of descent up to 15 or 20 feet per second (full scale), can be performed satisfactorily. Sustained vertical descent in still air probably will be more difficult to perform because of large random trim changes that become greater as the descent velocity is increased. A slight steady head wind or cross wind might be sufficient to eliminate the random trim changes.

  17. Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Cederborg, Gibson A.

    1948-01-01

    The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model. Scale-strength bottoms and simulated crumpled bottoms were used to reproduce probable damage to the fuselage. It was concluded that the airplane should be ditched at a landing attitude of about 5 deg with flaps full down. At this attitude, the maximum longitudinal deceleration should not exceed 2g and the landing run will be bout three fuselage lengths. Damage to the fuselage will not be excessive and will be greatest near the point of initial contact with the water.

  18. General problem of the airplane

    NASA Technical Reports Server (NTRS)

    Richard, Maurice; Richard, Paul

    1922-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.; Healy, Frederick M.

    1952-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Bowman, James S., Jr.

    1955-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1953-01-01

    Tests were made with a 1/8-scale dynamically similar model of the Chance Vought XF6U-1 airplane to study its behavior when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording time histories of the accelerations, and by taking motion pictures of the ditchings. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down attitude (12 deg). The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned. The underside of the fuselage will be critically damaged in a ditching and the airplane will dive violently after a run of about three fuselage lengths. Maximum longitudinal decelerations up to about 7g and maximum vertical accelerations up to about 5g will be encountered.

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; Windham, John O.

    1955-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Gillis, Clarence L; Mitchell, Jesse L

    1957-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    1959-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Fisher, Lloyd J.; McBride, Ellis E.

    1955-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Thompson, W. C.

    1973-01-01

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

  10. 77 FR 64704 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-23

    ... of two in-service occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the... occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed... new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD,...

  11. 77 FR 40307 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-09

    ... of two in-service occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the... Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss... earlier proposed airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D,...

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

    NASA Technical Reports Server (NTRS)

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

    1946-01-01

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

  13. Flight Tests of a 1/6-Scale Model of the Hawker P 1127 Jet VTOL Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1961-01-01

    An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/6-scale flying model of the Hawker P lIP7 jet vertical-take-off-and-landing (VTOL) airplane in hovering and transition flight. The model was powered by a counter-rotating ducted fan driven by compressed-air jets at the tips of the fan blades. In hovering flight the model was controlled by jet-reaction controls which consisted of yaw and pitch jets at the extremities of the fuselage and a roll jet on each wing tip. In forward flight the model was controlled by conventional ailerons and rudder and an all-movable horizontal tail. In hovering flight the model could be flown smoothly and easily, but the roll control was considered too weak for rapid maneuvering or hovering in gusty air. Transitions from hovering to normal forward flight and back to hovering could be made smoothly and consistently and with only moderate changes in longitudinal trim. The model had a static longitudinal instability or pitch-up tendency throughout the transition range, but the rate of divergence in the pitch-up was moderate and the model could be controlled easily provided the angle of attack was not allowed to become too high. In both the transition and normal forward flight conditions the lateral motions of the model were difficult to control at high angles of attack, apparently because of low directional stability at small angles of sideslip. The longitudinal stability of the model in normal forward flight was generally satisfactory, but there was a decided pitch-up tendency for the flap-down condition at high angles of attack. In the VTOL landing approach condition, with the jets directed straight down or slightly forward, the nose-down pitch trim required was greater than in the transitions from hovering to forward flight, but the longitudinal instability was about the same. Take-offs and landings in still air could be made smoothly although there was a slight unfavorable

  14. The Airplane Experiment.

    ERIC Educational Resources Information Center

    Larson, Lee; Grant, Roderick

    1991-01-01

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

  15. The Airplane Experiment.

    ERIC Educational Resources Information Center

    Larson, Lee; Grant, Roderick

    1991-01-01

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

  16. Investigation of the Spinning and Tumbling Characteristics of a 1/25-Scale Model of the Lockheed XFV-1 Airplane in the Langley 20-Foot Free-Spinning Tunnel

    NASA Technical Reports Server (NTRS)

    Lee, Henry A.

    1953-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/23-scale model of the Lockheed XFV-1 airplane to determine the effects of control setting and movement upon the erect-spin and recovery characteristics for a range of airplane loading conditions. A windmilling propeller was simulated on the model for some of the tests. The investigation included determination of the size of tail parachute required for emergency recovery from demonstration spins. The tumbling tendencies of the model were also investigated. The results indicated that any erect or inverted spin obtained on the airplane will be satisfactorily terminated if recovery is attempted by full rudder reversal accompanied by simultaneous lateral and longitudinal movement of the stick to neutral, The model test results showed that an 11.5-foot flat-type tail parachute (drag coefficient approximately 0.73) with a 27.5-foot towline will be effective as an emergency spin-recovery device during demonstration spins of the airplane. The model results also indicate that the airplane will not tumble for any.loading condition indicated possible.

  17. Longitudinal Stability and Control Characteristics at Transonic Speeds of a 1/30-Scale Model of the Republic XF-103 Airplane

    NASA Technical Reports Server (NTRS)

    Luoma, Arvo A.

    1954-01-01

    The longitudinal stability and control characteristics of a 1/30-scale model of the Republic XF-103 airplane were investigated in the Langley 8-foot transonic tunnel. The effect of speed brakes located at the end of the fuselage was also investigated. The main part of the investigation was made with internal flow in the model, but some data were obtained with no internal flow. The longitudinal stability and control at transonic-speeds appeared satisfactory. The transonic drag rise was small. The speed brakes had no adverse effects on longitudinal stability.

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

    NASA Technical Reports Server (NTRS)

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

    1972-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Klinar, Walter J.

    1946-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Rainey, A Gerald; Igoe, William B

    1958-01-01

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

  1. Low speed wind tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on an extended-range wide body tri-jet airplane model

    NASA Technical Reports Server (NTRS)

    Croom, D. R.; Vogler, R. D.; Thelander, J. A.

    1976-01-01

    An investigation was made in the Langley V/STOL tunnel to determine, by the trailing wing sensor technique, the effectiveness of various segments of the existing flight spoilers on an extended-range wide-body tri-jet transport airplane model when they were deflected as trailing-vortex-alleviation devices. On the transport model with the approach flap configuration, the four combinations of flight-spoiler segments investigated were effective in reducing the induced rolling moment on the trailing wing model by as much as 25 to 45 percent at downstream distances behind the transport model of 9.2 and 18.4 transport wing spans. On the transport airplane model with the landing flap configuration, the four combinations of flight-spoiler segments investigated were effective in reducing the induced rolling moment on the trailing wing model by as much as 35 to 60 percent at distances behind the transport model of from 3.7 to 18.4 transport wing spans, 18.4 spans being the downstream limit of distances used.

  2. 78 FR 5146 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Dive Speed Definition With Speed...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-24

    ... aerodynamic data are used. (a) From an initial condition of stabilized flight at V C /M C , the airplane is... and pilot-controlled drag devices may be used. (b) From a speed below V C /M C , with power to...

  3. 76 FR 14341 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-16

    ... failure condition includes consequential or cascading effects resulting from the first failure. B. Effects... systems that affect the airplane's structural performance, either directly or as a result of failure or... remain flutter free after certain failures. The regulations do not anticipate the use of systems...

  4. 76 FR 30523 - Special Conditions: Boeing Model 747-8/-8F Airplanes, Interaction of Systems and Structures

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-26

    ... consequential or cascading effects resulting from the first failure. B. Effects of Systems on Structures 1... airplane's structural performance, either directly or as a result of failure or malfunction. That is, the... failures. The regulations do not anticipate the use of systems that control flutter modes but do...

  5. 78 FR 70849 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-27

    ... with Class 3 Electronic Flight Bags (EFB) and wireless local area data networks (LAN) associated with the EFB architecture and existing airplane network systems. The applicable airworthiness regulations..., software-configurable avionics, and fiber-optic avionics networks. The proposed Class 3 EFB architecture...

  6. 78 FR 70848 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-27

    ... with Class 3 Electronic Flight Bags (EFB) and wireless local area data networks (LAN) associated with the EFB architecture and existing airplane network systems. The applicable airworthiness regulations..., software-configurable avionics, and fiber-optic avionics networks. The proposed Class 3 EFB architecture...

  7. 75 FR 32 - Special Conditions: Airbus Model A340 Series Airplanes; Seats With Non-Traditional, Large, Non...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-04

    ..., Airframe/Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601... flammability standards required of large, non-metallic panels in the cabin interior. At the time the applicable... cabin in the case of fire. These seats are considered a novel design for transport-category...

  8. 75 FR 43049 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-23

    ... BUS); or --ELEC EMERGENCY displayed on CAS (which means Electrical Emergency). The loss of airplane... EMERGENCY BUS); or --ELEC EMERGENCY displayed on CAS (which means Electrical Emergency). The loss of...: --DC BUS 1 OFF displayed on Crew Alerting System--CAS in conjunction with STBY HTR FAIL (which means...

  9. 75 FR 71346 - Special Conditions: Boeing Model 787-8 Airplane; Lightning Protection of Fuel Tank Structure To...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-23

    ... Traffic Controller Association (NATCA) requested the proposed special conditions be withdrawn since they... would be a practical way to implement new technology because a small number of airplane flights could be impacted by flight delays caused by an inoperative fuel tank inerting system. We have already addressed the...

  10. 76 FR 63851 - Special Conditions: Learjet Inc., Model LJ-200-1A10 Airplane, Pilot-Compartment View Through...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-14

    ... such an area during heavy-rain precipitation at airplane speeds up to 1.5 V SR1 . Hydrophobic windshield coatings may depend to some degree on airflow to maintain a clear-vision area. The heavy rain and... from light misting precipitation to heavy rain, at speeds from fully stopped in still air, to 1.5 V...

  11. 76 FR 437 - Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-05

    ... the airplane. * * * * * The corrective action is revising the Airworthiness Limitations Section (ALS... Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new...) Unless already done, do the following actions. (1) Before December 16, 2008, revise the ALS of the ICA...

  12. 76 FR 57625 - Special Conditions: Boeing Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-09-16

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

  13. 76 FR 7513 - Airworthiness Directives; The Boeing Company Model 747-400 and -400F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-10

    ... fiberglass reinforcing overcoat; and, for certain airplanes, installation of stiffening panels to the MEC... necessary, and installing a fiberglass reinforcing overcoat to the MEC drip shield. Additionally, for... stiffeners and the fiberglass reinforcing overcoat to the MEC drip shield; in accordance with the...

  14. 78 FR 11553 - Special Conditions: Embraer S.A., Model EMB-550 Airplane; Electronic Flight Control System...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-19

    ... Airplane; Electronic Flight Control System: Control Surface Awareness and Mode Annunciation AGENCY: Federal... control system. The applicable airworthiness regulations do not contain adequate or appropriate safety... a fly-by-wire electronic flight control system and no direct coupling from the flightdeck...

  15. 76 FR 69159 - Airworthiness Directives; The Boeing Company Airplanes Model 737-600, -700, -700C, -800, -900...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-08

    ..., -700C, -800, -900, and -900ER series airplanes. This proposed AD would require checking the escape slide... pilot valve regulator, installing a new firing cable and safety pin, and modifying the slide valise. This proposed AD was prompted by reports of escape slides failing to deploy from the forward and aft...

  16. 78 FR 68986 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-18

    ... modified by The Boeing Company, will have novel or unusual design features associated with the architecture... proposed architecture is novel or unusual for commercial transport airplanes by enabling connection to... system architecture or electronic access to aircraft systems. Furthermore, regulations and current system...

  17. 75 FR 70092 - Special Conditions: Bombardier Inc. Model CL-600-2E25 Airplane, Interaction of Systems and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-17

    ... Panels, No. 25-384-SC, dated August 12, 2009. 4. Exemptions: Exemption No. 7447, hydraulic-systems... flight. Certain elements of the control system, such as mechanical and hydraulic components, may use... Airplane, Interaction of Systems and Structures AGENCY: Federal Aviation Administration (FAA), DOT....

  18. 75 FR 82337 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    ... for the center override/jettison fuel pumps, and installing power control circuitry for the center ] override/jettison and main jettison fuel pumps. This proposed AD would also require installing new software... history of airplanes subject to those regulations, and existing maintenance practices for fuel...

  19. 75 FR 23579 - Airworthiness Directives; DASSAULT AVIATION Model FALCON 900EX and MYSTERE-FALCON 900 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-04

    ... FALCON 900EX and MYSTERE-FALCON 900 airplanes. This AD requires repetitive operational tests of the flap... the inboard flap jackscrews with new or reconditioned jackscrews; and repetitive measurement of the screw/nut play of the jackscrews on the inboard and outboard flaps to detect discrepancies, and...

  20. 76 FR 13534 - Airworthiness Directives; The Boeing Company Model 767-200, -300, -300F, and -400ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-14

    ... explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by April... tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and... tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion...