Science.gov

Sample records for airplanes model a319-111

  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. 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...

  3. 76 FR 61641 - Airworthiness Directives; Airbus Model A319-111, -112, and -132 Airplanes; Model A320-111, -211...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-05

    ... reported on the overwing refueling aperture (used to fill the fuel tank by gravity) on the wing top skin... reported on the overwing refueling aperture (used to fill the fuel tank by gravity) on the wing top skin... electrical bonding check between the gravity fill re-fuel adaptor and the top skin panels on the...

  4. 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.

  5. 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...

  6. 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...

  7. 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...

  8. 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...

  9. 78 FR 73993 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-10

    ... external to the airplane. Discussion The architecture and network configuration in the Cessna Model 680... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Cessna Model 680 Series Airplanes... conditions are issued for the Cessna Model 680 Series airplanes. These airplanes will have a novel or...

  10. 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.

  11. 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,...

  12. 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.

  13. 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

    ... Airplane; Full Authority Digital Engine Control (FADEC) System AGENCY: Federal Aviation Administration (FAA... issued for the Cirrus Design Corporation model SF50 airplane. This airplane will have a novel or unusual... Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901...

  14. 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...

  15. 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...

  16. 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:...

  17. 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...

  18. 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.

  19. 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...

  20. 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...

  1. 76 FR 10528 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... 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...

  2. 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:...

  3. 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...

  4. 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...

  5. 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

    ... Limited Model DHC-3 (Otter) Airplanes With Supplemental Type Certificate (STC) SA 09866SC AGENCY: Federal... DHC-3 (Otter) airplanes equipped with a Honeywell TPE331- 10 or -12JR turboprop engine installed per... for Viking Air Limited Model DHC-3 (Otter) airplanes equipped with a Honeywell TPE331-10 or...

  6. 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...

  7. 78 FR 65153 - Special Conditions: Learjet Model 45 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ...); 2. Operator business and administrative support (operator information services); 3. Passenger... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Learjet Model 45 Series Airplanes... conditions are issued for the Learjet Model 45 series airplanes. These airplanes will have a novel or...

  8. 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...

  9. 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...

  10. 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...

  11. 76 FR 1979 - Airworthiness Directives; The Boeing Company Model 757 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-12

    ... certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated...-16576; AD 2011-02-03] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Model 757 Airplanes... -300 series airplanes. This AD requires an inspection of the two spring arms in the spin...

  12. 76 FR 8607 - Airworthiness Directives; The Cessna Aircraft Company Model 750 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    ... Company Model 750 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule... requires revising the airplane flight manual. This AD was prompted by a report of a DC generator..., Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on...

  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

    ... introductory material also stated the service test requirement was removed for airplanes of 6,000 pounds... Airplane; Function and Reliability Testing; Withdrawal AGENCY: Federal Aviation Administration (FAA), DOT... notice granting special conditions for the Cirrus Design Corporation model SF50 airplane. We...

  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

    ... to be approved, the repair must meet the certification basis of the airplane. Material Incorporated... Model 737-100 and - 200 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... -200 series airplanes. This AD requires repetitive inspections for cracking and damaged fasteners...

  15. 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

    ... information services, than previous GALP airplane models. This may allow the exploitation of network security... Gulfstream G280 Airplane; Isolation or Aircraft Electronic System Security Protection From Unauthorized... connectivity of the passenger service computer systems to the airplane critical systems and data networks....

  16. 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.

  17. 78 FR 36084 - Special Conditions: The Boeing Company, Model 717-200 Series Airplanes; Seats With Inflatable...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-17

    ... flammability of the airbag material. The Boeing Model 717-200 series airplanes will use the similar airbag... Series Airplanes; Seats With Inflatable Lapbelts AGENCY: Federal Aviation Administration (FAA), DOT... the Boeing Model 717- 200 series airplanes. These airplanes will have a novel or unusual...

  18. 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

    ...) Model G280 Airplane, Limit Engine Torque Loads for Sudden Engine Stoppage AGENCY: Federal Aviation... conditions are issued for the Gulfstream Aerospace LP (GALP) model G280 airplane. This airplane will have a...: Federal Aviation Administration, Transport Airplane Directorate, Attn: Rules Docket (ANM-113), Docket...

  19. 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...

  20. 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

    ... similarly sized airplane fabricated from traditionally used metallic materials. The FAA and industry have... Airplane; Crashworthiness, Emergency Landing Conditions AGENCY: Federal Aviation Administration (FAA), DOT... Learjet Model LJ-200-1A10 airplane. This airplane will have novel or unusual design features when...

  1. 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

    ... maintenance of the airplane. The existing regulations and guidance material did not anticipate these types of... Series Airplanes; Aircraft Electronic System Security Protection From Unauthorized Internal Access AGENCY... conditions are issued for the Boeing Model 777- 200, -300, and -300ER series airplanes. These airplanes,...

  2. 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...

  3. 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

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

  4. 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...

  5. 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...

  6. 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...

  7. 78 FR 73995 - Special Conditions: Cessna Model 680 Series Airplanes; Aircraft Electronic System Security...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-10

    ... data busses and networks. A separate Cessna Model 680 project special condition addresses aircraft.... Discussion The integrated network configurations in the Cessna Model 680 series airplanes may allow increased... passenger entertainment and information services than previous airplane models. This may allow...

  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... is withdrawn. FOR FURTHER INFORMATION CONTACT: Carey O'Kelley, Aerospace Engineer, Airframe...

  9. 76 FR 37684 - Airworthiness Directives; Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Diamond Aircraft Industries GmbH Model (Diamond) DA 40 Airplanes Equipped With Certain Cabin Air Conditioning Systems AGENCY... inspections of the Diamond Model DA 40 airplanes equipped with a VCS installed per Premier Aircraft...

  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

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

  11. 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...

  12. 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...

  13. 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...

  14. 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

    ...; Isolation or Airplane Electronic System Security Protection From Unauthorized Internal Access AGENCY... diverse set of functions, including: Flight-safety related control and navigation systems, Airline...-550 airplanes. Isolation or Airplane Electronic System Security Protection From Unauthorized...

  15. 76 FR 14794 - Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security-Isolation or...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-18

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Boeing Model 747-8 Airplanes, Systems and Data Networks Security--Isolation or Protection From Unauthorized Passenger Domain Systems Access... special conditions are issued for Boeing Model 747-8 airplanes. This airplane will have novel or...

  16. 78 FR 76252 - Special Conditions: Airbus, Model A350-900 Series Airplane; Isolation or Protection of the...

    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... action proposes special conditions for Airbus Model A350- 900 series airplanes. These airplanes will have... an association, business, labor union, etc.). DOT's complete Privacy Act Statement can be found...

  17. 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

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series Airplane... conditions for Airbus Model A350- 900 series airplanes. These airplanes will have a novel or unusual design... the comment (or signing the comment for an association, business, labor union, etc.). DOT's...

  18. 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...

  19. 78 FR 63902 - Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-25

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Embraer S.A., Model EMB-550 Airplanes... for the Embraer S.A. Model EMB-550 airplane. This airplane will have a novel or unusual design feature... this rulemaking by sending written comments, data, or views. The most helpful comments reference...

  20. 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...

  1. 78 FR 49655 - Special Conditions: Embraer, S.A., Model EMB-550 Airplane; Side-Facing Seats; Installation of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-15

    ... Model EMB-550 airplane. The Model EMB-550 airplane is the first of a new family of jet airplanes... observing lower-leg flailing in typical high-speed video of the dynamic tests. This requirement complies... to load against the seat backs. If, during a side-facing-seat dynamic test, the flailing of...

  2. 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... 12 passengers. It is equipped with two Honeywell HTF7500-E medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust for...

  3. 76 FR 27239 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-11

    ... Company (Cessna) Model 172 Airplanes Modified by Supplemental Type Certificate (STC) SA01303WI AGENCY... products listed above. The numbering of paragraphs (j)(3), (j)(4), and (j)(5) in the Material Incorporated... airplane flight manual, and replacing the FADEC backup battery every 12 calendar months for Cessna...

  4. 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...

  5. 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......

  6. 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...

  7. 75 FR 82335 - Airworthiness Directives; APEX Aircraft Model CAP 10 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-30

    ... CAP 10 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... DAROIS-France, telephone: (33) 380 35 65 10; fax: (33) 380 35 65 15; e- mail: apex-aircraft.com . You may...) None. Applicability (c) This AD applies to APEX Aircraft Model CAP 10 airplanes, all serial...

  8. 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.

  9. 76 FR 8612 - Airworthiness Directives; Airbus Model A340-200, -300, -500, and -600 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    ...-200, -300, -500, and -600 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department... 2006-09-07, Amendment 39-14577 (71 FR 25919, May 3, 2006), for all Airbus Model A330-200 and -300, and A340-200 and -300 series airplanes, and A340-541 and -642 airplanes. That AD requires operators...

  10. 75 FR 81409 - Airworthiness Directives; The Boeing Company Model 737-200, -300, -400, and -500 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-28

    ... repair must meet the certification basis of the airplane. Material Incorporated by Reference (n) You must... Model 737-200, -300, -400, and -500 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT..., -300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking of...

  11. 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...

  12. 77 FR 69747 - Airworthiness Directives; The Boeing Company Model Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-21

    ... adds inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord... outboard chord at BS 727 and in the radius of the auxiliary chord on airplanes that were not affected by... radius of the auxiliary chord, for certain airplanes. That NPRM also proposed to remove the...

  13. 78 FR 66317 - Special Conditions: Learjet Inc. Model LJ-200-1A10; Airplane Fuselage Post-Crash Fire Survivability

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-05

    ... is the first airplane manufactured by Learjet Inc. to utilize advanced composite materials in the.... Model LJ-200-1A10; Airplane Fuselage Post-Crash Fire Survivability AGENCY: Federal Aviation... conditions for the Learjet Inc. Model LJ-200-1A10 airplane. This airplane will have a novel or unusual...

  14. 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...

  15. 76 FR 22005 - Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200 and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-20

    ...-16668; AD 2011-09-06] RIN 2120-AA64 Airworthiness Directives; Airbus Model A330-200 and -300 Series Airplanes, and Model A340-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration...

  16. 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...

  17. 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,...

  18. 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

    ... networks and systems, such as passenger entertainment and information services, than previous Gulfstream airplane models. This may allow the exploitation of network security vulnerabilities and increased risks... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace Corporation,...

  19. 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.

  20. 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...

  1. 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,...

  2. 76 FR 27863 - Airworthiness Directives; Airbus Model A318-112, A319-111, A319-112, A319-115, A319-132, A319-133...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-13

    ... been detected on terminal modules Part Number (P/N) NSA 937901M1604, manufactured by Deutsch, due to an... on terminal modules Part Number (P/N) NSA 937901M1604, manufactured by Deutsch, due to an... Number (P/N) NSA 937901M1604, manufactured by Deutsch, due to an insufficient crimping of the...

  3. 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...

  4. 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.

  5. 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...

  6. 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,...

  7. 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...

  8. 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...

  9. 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...

  10. 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,...

  11. 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...

  12. 78 FR 15874 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-13

    ...-112-AD; Amendment 39-17372; AD 2013-04-14] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of...

  13. 75 FR 25124 - Airworthiness Directives; The Boeing Company Model 737-200, -300, -400, and -500 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-07

    ... Model 737-200, -300, -400, and -500 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain Model 737-200, -300, -400, and -500 series airplanes. This proposed AD would require...) None. Applicability (c) This AD applies to The Boeing Company Model 737-200, -300, - 400, and...

  14. 77 FR 69571 - Special Conditions: Embraer S.A., Model EMB-550 Airplane, Limit Pilot Forces for Sidestick Control

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-20

    ... features: The Embraer S.A. Model EMB-550 airplane is equipped with a sidestick controller instead of a... The Embraer S.A. Model EMB-550 airplane is equipped with a sidestick controller instead of a... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Embraer S.A., Model EMB-550...

  15. 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.

  16. 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...

  17. 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...

  18. 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...

  19. 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.

  20. 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.

  1. 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...

  2. 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...

  3. 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... 300 BD-100 Time Limits/Maintenance Checks Manual. The actions described in this service information... all Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes, certificated in any category....

  4. 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,...

  5. 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...-300 series airplane experienced a rapid decompression when the lap joint at stringer S-4L between BS... at stringers S-4L and S-4R. This action was prompted by a report indicating that a Model...

  6. 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...

  7. 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

    ... Administration 14 CFR Part 25 Special Conditions: Boeing Model 747-8/-8F Airplanes, Systems and Data Networks Security--Protection of Airplane Systems and Data Networks From Unauthorized External Access AGENCY... to or by external network sources. Discussion The Model 747-8/-8F architecture and...

  8. 76 FR 41045 - Special Conditions; Gulfstream Aerospace LP (GALP) Model G250 Airplane, Design Roll-Maneuver...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions; Gulfstream Aerospace LP (GALP) Model... the Gulfstream Aerospace LP (GALP) Model G250 airplane. This airplane will have novel or...

  9. 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...

  10. 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...

  11. 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....

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-23

    .... 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...

  13. 75 FR 69606 - Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 0070 and 0100 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-15

    ... 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.... * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the...

  14. 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...

  15. 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...

  16. 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...

  17. 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...

  18. 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.

  19. 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... Bombardier Aerospace Model BD-500-1A10 and BD-500-1A11 airplanes are equipped with a sidestick controller... conditions for the Bombardier Aerospace Model BD-500-1A10 and BD-500-1A11 airplanes. These airplanes...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-19

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

  1. 76 FR 65103 - Special Conditions: Gulfstream Aerospace Corporation, Model GIV-X Airplane; Aircraft Electronic...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-20

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace Corporation, Model... comments. SUMMARY: These special conditions are issued for the Gulfstream Aerospace Corporation Model GIV-X... connectivity capabilities of the airplane's computer systems and networks, which may allow access by...

  2. 77 FR 36123 - Special Conditions: Gulfstream Aerospace LP (GALP), Model Gulfstream G280 Airplane; Aircraft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-18

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace LP (GALP), Model... comments. SUMMARY: These special conditions are issued for the Gulfstream Aerospace LP, Model Gulfstream... architecture and connectivity capabilities of the airplane's computer systems and networks, which may...

  3. 76 FR 25229 - Special Conditions: Gulfstream Aerospace LP (GALP) Model G250 Airplane, Dynamic Test Requirements...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-04

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Gulfstream Aerospace LP (GALP) Model... special conditions are issued for the Gulfstream Aerospace LP (GALP) model G250 airplane. This...

  4. 78 FR 76248 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ... also appropriate for the Model A350-900 series side stick controller. Applicability As discussed above...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controller AGENCY: Federal Aviation Administration (FAA),...

  5. 78 FR 67077 - Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controllers

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-08

    ... Federal Aviation Administration 14 CFR Part 25 Special Conditions: Airbus, Model A350-900 Series Airplane; Side Stick Controllers AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed special conditions. SUMMARY: This action proposes special conditions for the Airbus Model A350-900...

  6. 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...

  7. 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...

  8. 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....

  9. 78 FR 76775 - Special Conditions: Airbus, Model A350-900 Series Airplane; Lightning Protection of Fuel Tank...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-19

    ...This action proposes special conditions for the Airbus Model A350-900 series airplanes. These airplanes will have a novel or unusual design feature(s) that will incorporate a nitrogen generation system (NGS) for all fuel tanks that actively reduce flammability exposure within the fuel tanks significantly below that required by the fuel tank flammability regulations. Among other benefits, the......

  10. 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

    ...These special conditions are issued for the Boeing Model 777- 200, -300, and -300ER series airplanes. These airplanes as modified by the ARINC Aerospace Company will have a novel or unusual design feature, specifically the installation of rechargeable lithium ion batteries and battery system that will be used on an International Communications Group (ICG) ePhone cordless cabin handset. The......

  11. 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......

  12. 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

    ...'s rearward (rebound) motion. So to limit abdominal injury risk in side-facing seats, the lap belt...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 Special Conditions: Embraer, S.A... action proposes special conditions for the Embraer S.A. Model EMB-550 airplane. This airplane will have...

  13. 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... equipped with two Honeywell HTF7500-E medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust for normal takeoff. The primary...

  14. 76 FR 41142 - Special Conditions; Cessna Aircraft Company Model M680 Airplane; Lithium-ion Battery Installations

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-13

    ... also considering the use of this Lithium-battery technology in several ] other auxiliary-battery... (c)(4), basically reworded the CAR requirements. Increased use of Ni-Cd batteries in small airplanes... proposed use of rechargeable Lithium batteries for equipment and systems on the Model 680 airplane...

  15. 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....

  16. 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...

  17. 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...

  18. 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...

  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... 2. The FAA amends Sec. 39.13 by adding the following new AD: 2011-14-12 Saab AB, Saab Aerosystems... applies to all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, certificated in any category....

  20. 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... 2. The FAA amends Sec. 39.13 by adding the following new AD: 2011-05-13 Saab AB, Saab Aerosystems... applies to all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, certificated in any category....

  1. 75 FR 32863 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-10

    ... flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and... October 15, 2009, into the normal procedures section of the aircraft flight manual (AFM). (ii) Within 12... Directives; PILATUS AIRCRAFT LTD. Model PC-12/47E Airplanes AGENCY: Federal Aviation Administration...

  2. 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;...

  3. 76 FR 17364 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-29

    ... Model FALCON 7X Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Building Ground Floor, Room W12-40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m... the Internet at http://www.regulations.gov ; or in person at the Docket Operations office between 9...

  4. 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...-30, West Building Ground Floor, Room W12-40, 1200 New Jersey Avenue, SE., Washington, DC, between 9...

  5. 75 FR 30282 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-01

    ...-008-AD; Amendment 39-16312; AD 2010-11-07] RIN 2120-AA64 Airworthiness Directives; Quartz Mountain... Quartz Mountain Aerospace, Inc. Model 11E airplanes. This AD requires you to clean and lubricate the... publications listed in this AD. ADDRESSES: Quartz Mountain Aerospace, Inc. is in liquidation. For...

  6. 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... Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402-2206..., Aerospace Engineer, Continued Operational Safety and Certificate Management Branch, ACE- 102A, FAA,...

  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. 75 FR 38001 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-01

    ...-073-AD; Amendment 39-16352; AD 2010-14-07] RIN 2120-AA64 Airworthiness Directives; The Boeing Company...). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747 airplanes. That AD currently requires repetitive inspections of the...

  9. 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...

  10. 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...

  11. 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...

  12. 76 FR 36390 - Airworthiness Directives; The Boeing Company Model 747SP Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-22

    ... power control modules (PCM). This proposed AD was prompted by a report of a rudder hard-over event on a... rudder PCM manifold, which could result in a hard-over of the rudder surface leading to an increase in... of a Model 747-400 series airplane of a lower rudder hard-over event caused by a lower rudder...

  13. 76 FR 31454 - Special Conditions: Gulfstream Model GVI Airplane; Automatic Speed Protection for Design Dive Speed

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ... equipped with a high speed protection system that limits nose down pilot authority at speeds above V C /M C... certification of other airplane models. Discussion Gulfstream proposes to reduce the speed margin between V C and V D required by Sec. 25.335(b), based on the incorporation of a high speed protection system...

  14. 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....

  15. 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...

  16. 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...

  17. 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,...

  18. 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...

  19. 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...

  20. 75 FR 12468 - Airworthiness Directives; Quartz Mountain Aerospace, Inc. Model 11E Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-16

    .... The airplane was operated by a student pilot, who had trouble flying the airplane when this occurred... contamination. This condition, if not corrected, could lead to difficulty controlling the airplane in...

  1. 77 FR 55163 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-07

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340- 300 series airplanes; and Model A340-541 airplanes and Model A340-642 airplanes. That NPRM proposed to require performing...

  2. 77 FR 37797 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-25

    ...-059-AD; Amendment 39-17092; AD 2012-12-12] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes.... SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 series airplanes; Airbus Model A330-200 Freighter series airplanes; Airbus Model A330-300 series airplanes; Airbus...

  3. 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...

  4. 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.

  5. 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.

  6. 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...

  7. 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.

  8. 78 FR 21227 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-10

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final...-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 airplanes and Model A340- 642 airplanes. This AD was prompted by reports of cracks in the bogie pivot pin caused...

  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

    ... airplanes. These airplanes will have a novel or unusual design feature(s) associated with a braking system...-900 series airplane is equipped with a braking system that affects the airplane's pivoting behavior. During pivoting the braking system inhibits braking on some wheels. Title 14 Code of Federal...

  10. 77 FR 47267 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-08

    ... Model 747-200B series airplanes having a stretched upper deck. The existing AD currently requires...-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched..., and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper...

  11. 77 FR 5195 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-02

    ... series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The original NPRM...; and Model 747-200B series airplanes having a stretched upper deck. The original NPRM was published in... series airplanes; and Model 747-200B series airplanes having a stretched upper deck; certificated in...

  12. 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...

  13. 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.

  14. 78 FR 78694 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-27

    ...-223-AD; Amendment 39-17704; AD 2013-25-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... series airplanes, and Model A340-200 and -300 series airplanes. AD 2009-24-09 required a repetitive... ] hydraulic systems on airplanes that have had a certain modification embodied during production or...

  15. 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...

  16. 77 FR 48425 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-14

    ...-225-AD; Amendment 39-17152; AD 2012-16-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes... freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted... circuit for the fuel pumps for the center fuel tanks for certain airplanes, and center and rear fuel...

  17. 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...

  18. 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...

  19. 77 FR 50411 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-21

    ... Material Specification (BMS) 8-39 urethane foam, and a report from the airplane manufacturer that airplanes... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM... 747SP series airplanes; Model 767-200, -300, -300F, and -400ER series airplanes; and Model...

  20. 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.

  1. 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.

  2. 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.

  3. 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

    ... navigation systems (aircraft control domain); 2. Operator business and administrative support (operator... electronic system security protection against, access by unauthorized sources internal to the airplane. The... Airplanes; Isolation or Security Protection of the Aircraft Control Domain and the Airline...

  4. 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...

  5. 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.

  6. 75 FR 38947 - Airworthiness Directives; Airbus Model A330-200 and A330-300 Series Airplanes, and Model A340-200...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-07

    ...-200 and A330-300 Series Airplanes, and Model A340-200, A340-300, A340-500, and A340-600 Series... A330-200 and A330-300 series Airbus Mandatory Service January 20, 2010. airplanes. Bulletin A330-34-3232, including Appendix 01. Model A340-200 and A340-300 series Airbus Mandatory Service January...

  7. 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.

  8. 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.

  9. 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.

  10. 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...

  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...

  12. 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...

  13. 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...

  14. 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...

  15. 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...

  16. 76 FR 40291 - Airworthiness Directives; Learjet Inc. Model 45 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-08

    ... potential for fatigue cracking of the end cap of the MLG prior to the published life limitation. We are proposing this AD to prevent fatigue cracking of the end cap of the MLG, which could result in the failure... landing gear actuator was determined using fatigue testing during the Model 45 certification; however,...

  17. 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:...

  18. 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...

  19. 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.

  20. 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

  1. 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...

  2. 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.

  3. 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...

  4. 75 FR 55461 - Airworthiness Directives; Bombardier, Inc. Model DHC-8-200 and DHC-8-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-13

    .... Model DHC-8-200 and DHC-8-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department... the valve spring installed, the flapper valve is held closed by the valve spring, preventing gravity... spring, preventing gravity feed. In the event of scavenge system failure, the collector tank fuel...

  5. 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...

  6. 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...

  7. 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,...

  8. 75 FR 43101 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-23

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

  9. 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...

  10. 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...

  11. 75 FR 6865 - Airworthiness Directives; The Boeing Company Model 737-700 (IGW) Series Airplanes Equipped With...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-12

    ... procedures for modifying the auxiliary fuel system (AFS). The modification of the auxiliary fuel cells of the... Model 737-700 (IGW) Series Airplanes Equipped With Auxiliary Fuel Tanks Installed in Accordance With... modification of PATS Aircraft, LLC, auxiliary fuel tanks. This proposed AD results from fuel system...

  12. 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.

  13. 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...

  14. 76 FR 31459 - Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-01

    ...-208-AD; Amendment 39-16705; AD 2011-11-06] RIN 2120-AA64 Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Avro 146-RJ Airplanes AGENCY: Federal Aviation Administration (FAA..., prompted by a crack found at the top of the Nose Landing Gear (NLG) oleo, BAE Systems Operations) Ltd...

  15. 75 FR 53855 - Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-02

    ...-226-AD; Amendment 39-16423; AD 2010-18-10] RIN 2120-AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes AGENCY: Federal Aviation Administration (FAA... Applicability that have been modified to freighter configuration in accordance with BAE Systems modification...

  16. 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 &...

  17. 75 FR 16646 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-02

    ... during a production flight test where the proximity-sensor electronic unit (PSEU) failed. This resulted... incident during a production flight test where the proximity-sensor electronic unit (PSEU) failed. This... recent type certificate data sheet for the affected airplane models. Conclusion We reviewed the...

  18. 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...

  19. 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...

  20. 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...

  1. 75 FR 27966 - Airworthiness Directives; The Boeing Company Model 747-400 and 747-400D Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... certain Model 747-400 and 747-400D series airplanes. This proposed AD would ] require installing aluminum... November 4, 2009. The service bulletin describes procedures for installing aluminum gutter reinforcing... drip shield aluminum gutter, in accordance with Work Package 1 of the Accomplishment Instructions...

  2. 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...

  3. 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

    ... a derivative of the 747-400. The Model 747-8 is a four-engine jet transport airplane that will have a maximum takeoff weight of 975,000 pounds, new General Electric GEnx -2B67 engines, and the... extension packed at the toe end of the escape slide. During normal operation, the extension portion...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-16

    ... 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...

  5. 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...

  6. 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

    ... module (CRM). The applicable airworthiness regulations do not contain adequate or appropriate safety... installation of a lower lobe pilot crew rest module (CRM) in Boeing Model 767-300 series airplanes. The CRM..., will be provided for each occupant permitted in the CRM. The CRM is intended to be occupied only...

  7. 76 FR 72863 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-28

    ... (for Model 707 airplanes, and Model 720 and 720B series airplanes). Determine Material of the... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-100 long body, -200, -100B long body, and -100B short body series airplanes; Model 707-300,...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-06

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

  9. 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.

  10. 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.

  11. 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.

  12. 78 FR 46543 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-01

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes...: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This proposed AD was prompted by reports of...

  13. 75 FR 7557 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-22

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

  14. 76 FR 17022 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-28

    ... at which the airplane can develop a lift force normal to the flight path and equal to its weight when... minimum calibrated airspeed at which the airplane can develop a lift force normal to the flight path and... likely to be mistaken for natural stall identification. (3) No uncommanded lateral or directional...

  15. 76 FR 8917 - Special Conditions: Gulfstream Model GVI Airplane; Automatic Speed Protection for Design Dive Speed

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-16

    ... Gulfstream GVI airplane. This airplane will have novel or unusual design features when compared to the state... design features include a high speed protection system. These proposed special conditions contain the... GVI because of a novel or unusual design feature, special conditions are prescribed under...

  16. 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...

  17. 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...

  18. 78 FR 7261 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-01

    ...-070-AD; Amendment 39-17332; AD 2013-02-11] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes.... SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203 airplanes. This... Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125; fax...

  19. 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.

  20. 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.

  1. 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.

  2. 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.

  3. 77 FR 55681 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-11

    ... Material of the Components of the Horizontal Stabilizer For airplanes identified in Boeing 707 Alert...-17176; AD 2012-17-13] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY... -100B short body series airplanes; Model 707-300, -300B, -300C, and - 400 series airplanes; and...

  4. 78 FR 28128 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-14

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a... airplanes. This AD was prompted by reports of two in-service occurrences on Model 737-400 airplanes of total..., inability to restart the engines, and consequent forced landing of the airplane. DATES: This AD is...

  5. 76 FR 68666 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-07

    ... Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain The Boeing Company Model 737-100, -200, -200C, and -300 series airplanes. This proposed AD was prompted by a report from the airplane manufacturer that airplanes were assembled with...

  6. 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.

  7. 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.

  8. 76 FR 36870 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-23

    ...; Design Roll Maneuver Requirement for Electronic Flight Controls AGENCY: Federal Aviation Administration... electronic flight control system that provides roll control of the airplane through pilot inputs to the flight computers. These special conditions contain the additional safety standards that the...

  9. 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.

  10. 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...

  11. 76 FR 35344 - Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Model P2006T Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-17

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

  12. 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...

  13. 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...

  14. 76 FR 10529 - Special Conditions: Gulfstream Model GVI Airplane; Electronic Systems Security Protection From...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-25

    ... systems and networks may result in security vulnerabilities to the airplane's systems. The applicable... may allow the exploitation of network security vulnerabilities resulting in intentional or...; Electronic Systems Security Protection From Unauthorized External Access AGENCY: Federal...

  15. 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...

  16. 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.

  17. 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.

  18. 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.)

  19. 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.

  20. 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.

  1. 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.

  2. 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.

  3. 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.

  4. 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

  5. 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

  6. 77 FR 58787 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-24

    ... Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. The existing... would expand the applicability by adding Model CL-600- 2C10 (Regional Jet Series 700, 701, &...

  7. 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.

  8. 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.

  9. 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...

  10. 75 FR 22514 - Airworthiness Directives; The Boeing Company Model 747-200B Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-29

    ... Boeing to the stretched upper deck (SUD) configuration require inspection for cracking of the stringer 6... stretched upper deck (SUD) configuration require inspecting the stringer 6 lap joint upper fastener row for... results from reviews done by Boeing, which show that airplanes modified to the stretched upper deck...

  11. 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... results from (1) reports of fuel leaks from certain drain locations of the slat track housing near the engine exhaust nozzle, which could result in a fire when the airplane is stationary, or taxiing at...

  12. 75 FR 61999 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

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

  13. 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... low-wing, five-plus-two-place (2 children), single-engine turbofan- powered aircraft. It incorporates.... The turbofan engine is mounted on the upper fuselage/tail cone along the aircraft centerline. It...

  14. 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 gear, and a V-tail. The turbofan engine is mounted on the upper fuselage/tail cone along the...

  15. 76 FR 41659 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-07-15

    ... nor increase the scope of the AD. Costs of Compliance We estimate that this AD affects 215 airplanes of U.S. registry. The new requirements of this AD add no additional economic burden. The current costs for this AD are repeated below for the convenience of affected operators. The actions that...

  16. 75 FR 77793 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-14

    .... The new requirements of this proposed AD add no additional economic burden. The current costs for this...) paragraph (l). paragraph (g) paragraph (m). Costs of Compliance There are about 772 airplanes of the... labor rate of $85 per work-hour. Based on these figures, the estimated cost of the currently...

  17. 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

    ... information describes procedures for repetitive detailed inspections or surface high frequency eddy current... Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs... estimate the following costs to comply with this proposed AD: Estimated Costs Cost on U.S. Action...

  18. 75 FR 39472 - Airworthiness Directives; Eclipse Aerospace, Inc. Model EA500 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-09

    ... FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for... 06 122205, Revision 03. (ii) Avionics upgrade to AVIO NG + 1.5 Configuration and Aircraft Flight... require incorporating changes to the electronic flight information system and the airplane flight...

  19. 75 FR 27969 - Airworthiness Directives; The Boeing Company Model 737-100 and -200 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-19

    ... cracking and damaged fasteners of certain fuselage frames and stub beams, and corrective actions if... the inboard chord fastener hole of the frame at body station 639, stringer S-16, and corrective... inspections for the repaired or modified frame only. For airplanes on which the modification or repair is...

  20. 75 FR 66659 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-29

    ... associated with a structural fatigue phenomenon of the rear spar internal angle and the tee fitting located...-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056... programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of...

  1. 75 FR 39863 - Airworthiness Directives; Airbus Model A310 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-13

    ... programme is necessary to detect and prevent damage associated with a structural fatigue phenomenon of the... referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton... INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport...

  2. 76 FR 1983 - Airworthiness Directives; The Boeing Company Model MD-11 and MD-11F Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-12

    ... general visual inspection for correct installation of the self-adhering high-temperature electrical.... The SNPRM proposed to revise the original NPRM by adding, for certain airplanes, a general visual... 60 months after the effective date of this AD, perform a general visual inspection to detect...

  3. 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...

  4. 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...

  5. 76 FR 22828 - Airworthiness Directives; The Boeing Company Model 737-700 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-25

    ... certain airplanes, this proposed AD would also require moving certain rows of passenger seats. For certain... and corrective actions if necessary, and moving certain rows of passenger seats. This proposed AD... moving certain rows of seats. The corrective actions include modifying the seat tracks. We have...

  6. 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...

  7. 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...

  8. 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...

  9. 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...

  10. 76 FR 3854 - Airworthiness Directives; REIMS AVIATION S.A. Model F406 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-21

    ... adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by... airplane. The proposed AD would require actions that are intended to address the unsafe condition...

  11. 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...

  12. 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...

  13. 75 FR 80735 - Special Conditions: Gulfstream Model GVI Airplane; High Incidence Protection

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-23

    ... accommodate any reduction in stalling angle of attack resulting from flight in the atmospheric icing... weight; S = Aerodynamic reference wing area; and q = Dynamic pressure. (e) V SR must be determined with... controlled transport airplanes. 7. Atmospheric Disturbances--Operation of the high incidence...

  14. 75 FR 70863 - Airworthiness Directives; The Boeing Company Model 747 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-19

    ... 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 (MOV...). This service bulletin clarifies the procedure for measuring the electrical bond resistance, and...

  15. 76 FR 8319 - Special Conditions: Gulfstream Model GVI Airplane; Design Roll Maneuver Requirement for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-14

    ... airplanes. These design features include an electronic flight control system that provides roll control of... Design Features The GVI is equipped with an electronic flight control system that provides roll control... of an electronic flight control system. Discussion of Proposed Special Conditions The GVI is...

  16. 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...

  17. 76 FR 22298 - Airworthiness Directives; Cessna Aircraft Company (Cessna) Model 172 Airplanes Modified by...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-21

    ... engine control (FADEC) backup 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 AD... NPRM proposed to require installing a FADEC backup battery, replacing the supplement pilot's...

  18. 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...

  19. 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...

  20. 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...

  1. 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...

  2. 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

    ... engine mounts and the supporting structures must be designed to withstand a ``limit engine torque load... occur about once in the lifetime of any airplane. Section 25.305 requires that supporting structures be... of producing much higher transient loads on the engine mounts and supporting structures. As a...

  3. 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

    ... of any airplane. Section 25.305 requires that supporting structures be able to support limit loads without detrimental permanent deformation, meaning that supporting structures should remain serviceable... higher transient loads on the engine mounts and supporting structures. As a result, modern high...

  4. 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...

  5. 75 FR 15357 - Airworthiness Directives; The Boeing Company Model 767 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-03-29

    ... airplanes. This proposed AD would require repetitive inspections to detect fatigue cracking in the upper... this AD to detect and correct fatigue cracking in the upper wing skin at the fastener holes common to... October 28, 1999. Further Boeing analysis has determined the cracks to be a result of fatigue due...

  6. 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...

  7. 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

    ... maintenance of the airplane. The existing regulations and guidance material did not anticipate this type of... the safety and maintenance of the airplane. The existing regulations and guidance material did not... Series Airplanes; Aircraft Electronic System Security Protection From Unauthorized External Access...

  8. 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.

  9. 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.

  10. 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.

  11. 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.

  12. 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.

  13. 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.

  14. 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...

  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. 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.

  17. 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.

  18. 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.

  19. 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.

  20. 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.

  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. 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.

  3. 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...

  4. 75 FR 54536 - Airworthiness Directives; Airbus Model A330-200 and -300 and A340-200 and -300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-08

    ... 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 and A340-200 and -300 Series Airplanes AGENCY: Federal Aviation Administration (FAA),...

  5. 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...

  6. 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...

  7. 77 FR 21420 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-10

    ... Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 680 airplanes. This...-feed wiring, and revising the airplane flight manual to include procedures to use when the left...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-19

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM... Boeing Company Model 777-200 and -300 series airplanes. AD 2012-12-08 requires an inspection for the part... determined that additional airplanes may be subject to the identified unsafe condition. This proposed...

  10. 77 FR 46343 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-03

    ... Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM...-400D, 747-400F, 747SR, and 747SP series airplanes; and certain Model 757-200, -200PF, and -300 series airplanes. The existing AD currently requires replacing the control switches of the forward, aft, and...

  11. 78 FR 78292 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-26

    ... 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 7X airplanes. AD 2011-13-07 requires revising the airplane flight manual (AFM)...

  12. 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...

  13. 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;...

  14. 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...

  15. 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.

  16. 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

    .... This airplane will have novel or unusual design features when compared to the state of technology... flight computers. These special conditions contain the additional safety standards that the Administrator... airplane through pilot inputs to the flight computers. ] Discussion The 747-8/-8F is equipped with...

  17. 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

    ... part 34 and the noise certification requirements of 14 CFR part 36. Special conditions, as defined in... end. The airplane is equipped with an electronic sensor that evaluates the attitude of the airplane... slide in its normal attitude and will ensure that the slide can function in its extended mode at...

  18. 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

    ... features, specifically distributed electrical and electronic equipment bays in pressurized areas of the... straightforward airplane flight manual procedure. In distributed electrical/electronic bay installations it is not...-550 airplane has distributed electrical and electronic equipment bays that were not envisioned at...

  19. 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...

  20. 76 FR 4056 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-24

    ... these airplanes. This AD supersedes Emergency AD 2011-01-51, requires an immediate functional test of..., with noted exceptions, for the return/ position of the airplane to a home base, hangar, maintenance... reports prompted us to issue Emergency AD 2011-01-51 on December 18, 2010, to require an...

  1. 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...

  2. 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

    ... state of technology envisioned in the airworthiness standards for transport category airplanes. These... name of the individual sending the comment (or signing the comment for an association, business, labor... Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue...

  3. 75 FR 8554 - Airworthiness Directives; The Boeing Company Model 747-100, -200B, and -200F Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-25

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

  4. 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.

  5. 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

  6. 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.

  7. 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.

  8. 76 FR 18022 - Airworthiness Directives; The Boeing Company Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-04-01

    ... Model DC-9-14, DC-9- 15, and DC-9-15F Airplanes; and DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series..., Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT...) This AD applies to The Boeing Company Model DC-9-14, DC-9- 15, DC-9-15F, DC-9-21, DC-9-31,......

  9. 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.

  10. 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.

  11. 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.

  12. 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.

  13. 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.

  14. 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

  15. 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...

  16. 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.

  17. 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.

  18. 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.

  19. 76 FR 24832 - Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, A330-300...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-03

    ...-201, -202, -203, - 223, and -243 Airplanes, A330-300 Series Airplanes, A340-200 Series Airplanes, and A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... some rudders fitted on A330 and A340-200/-300 aeroplanes. An extended de-bonding, if not detected...

  20. 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.

  1. 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

    ... combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of... center fuel tank explosion and consequent loss of the airplane. Compliance (e) Comply with this AD...

  2. 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,...

  3. 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...

  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

    ..., specifically distributed electrical and electronic equipment bays in pressurized areas of the airplane. Older... manual procedure. In distributed electrical/electronic bay installations it is not as straightforward... incorporate the following novel or unusual design features: Distributed electrical and electronic...

  5. Testing a Windmill Airplane ("autogiro")

    NASA Technical Reports Server (NTRS)

    Seiferth, R

    1927-01-01

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

  6. 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.

  7. 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.

  8. 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.

  9. 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.

  10. 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.

  11. 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.

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-18

    ... requires replacing the control switches of the forward, aft, and nose cargo doors of Model 747 airplanes; and requires replacing the control switches of cargo doors 1 and 2 of Model 757 series airplanes. This... continue to require replacing the control switches of the forward, aft, and nose cargo doors of Model...

  14. 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

  15. 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.

  16. 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.

  17. 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.

  18. 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.

  19. 76 FR 8610 - Airworthiness Directives; Airbus Model A340-200, -300, -500, and -600 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-02-15

    ... A340-200, -300, -500, and -600 Series Airplanes AGENCY: Federal Aviation Administration (FAA...: Section 2-1 --A340-200/300 1-102 11 February 2009. Airworthiness Limitations. Section 2-2 --A340-500/600...

  20. 75 FR 2057 - Airworthiness Directives; Airbus Model A340-200 and A340-300 Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-14

    ...-200 and A340-300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... the A340-200/300 fleet has shown that the current utilization rate of the aeroplanes is different from...-200/300 fleet has shown that the current utilization rate of the aeroplanes is different from...

  1. 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

    ... also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 354 airplanes of U.S. registry. This new AD adds no new costs to affected operators. The current costs for this AD are repeated for the convenience of affected...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-17

    ... continuous electrical power to operate the control system. The current 14 CFR part 25.1351(d), ``Operation without normal electrical power,'' requires safe operation in VFR conditions for at least five minutes... Airplane, Operation Without Normal Electrical Power AGENCY: Federal Aviation Administration (FAA),...

  3. 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...

  4. 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

    ... requirements of 14 CFR part 36. Special conditions, as defined in Sec. 11.19, are issued under Sec. 11.38, and... airplane in level attitude and in each attitude resulting from the collapse of one or more legs of...

  5. 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

    ... conditions, as defined in 14 CFR 11.19, in accordance with Sec. 11.38, and they become part of the type...-induced, upsets resulting in initiation of the dive from non-symmetric attitudes; or that the airplane is... at a flight path 15 degrees below the initial path (or at the steepest nose down attitude that...

  6. 75 FR 1297 - Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-01-11

    ... rail of the slat main tracks for debris, replacing the bolts of the aft side guide with new bolts, and removing any debris found in the slat can. This proposed AD also would remove airplanes from the... consequent fire. DATES: We must receive comments on this proposed AD by February 25, 2010. ] ADDRESSES:...

  7. 77 FR 26663 - Airworthiness Directives; The Boeing Company Model 767-200, -300, -300F, and -400ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-05-07

    ... inspections to detect cracking or corrosion of the fail-safe straps between the side fitting of the rear spar... applicability; and adds an inspection for cracking in the fail-safe strap, and repair or replacement if necessary. This AD was prompted by additional reports of cracks in 51 fail-safe straps on 41 airplanes;...

  8. 75 FR 59606 - Airworthiness Directives; Pacific Aerospace Limited Models FU24-954 and FU24A-954 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-28

    ...-051-AD; Amendment 39-16453; AD 2010-20-18] RIN 2120-AA64 Airworthiness Directives; Pacific Aerospace..., Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106...: 2010-20-18 Pacific Aerospace Limited: Amendment 39-16453; Docket No. FAA-2010-0941;...

  9. 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...

  10. 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

    ... takeoff weight of 82,011 pounds. The applicable airplane regulations, currently approved under Title 14, Code of Federal Regulations (14 CFR) part 25, do not require seats to meet the more-stringent... applicable airworthiness regulations do not contain adequate or appropriate safety standards for this...

  11. 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...

  12. 78 FR 52107 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-22

    ... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal Aviation... lithium ion batteries and battery system that will be used on an International Communications Group (ICG... applied for a supplemental type certificate for installing equipment that uses rechargeable lithium...

  13. 75 FR 42592 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-22

    ..., October 1, 2009). 767-200, -300, and - for fatigue cracking 300F series airplanes. and corrosion of the... midspar fitting tangs. We are issuing this AD to detect and correct fatigue cracking in the primary strut... specified in that AD are intended to prevent fatigue cracking in the primary strut structure and...

  14. 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...

  15. 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...

  16. 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...

  17. 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...

  18. 75 FR 34663 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-18

    ... series airplanes. The original NPRM would have required installing Teflon sleeving under the clamps of... 3956). That original NPRM proposed to require installing Teflon sleeving under the clamps of the wire... for installing Teflon sleeving under the clamps of the power feeder wire bundles routed along...

  19. 75 FR 78588 - Airworthiness Directives; The Boeing Company Model 777-200, -300, and -300ER Series Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-16

    ..., -300, and -300ER series airplanes. This AD requires installing Teflon sleeving under the clamps of... FR 3956, January 29, 2007) proposed to require installing Teflon sleeving under ] the clamps of... specified, unless the actions have already been done. Corrective Actions (Installing Teflon Sleeving,...

  20. 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

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

  1. 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

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

  2. 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....

  3. 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...

  4. 78 FR 76249 - Special Conditions: Airbus, Model A350-900 Series Airplane; Flight Envelope Protection: Normal...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-17

    ... feature(s) associated with a flight control system that prevents the pilot from inadvertently or... unique in that traditional airplanes with conventional flight control systems (mechanical linkages) are... using the Airbus flight control system. Under Title 14, Code of Federal Regulations (14 CFR)...

  5. 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...

  6. 77 FR 64025 - Special Conditions: Airbus Model A318, A319, A320, and A321 Series Airplanes; Interaction of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-18

    ..., and A321 Series Airplanes; Interaction of Systems and Structures AGENCY: Federal Aviation... interactions of systems and structures. Airbus requested, and FAA agrees, that these special conditions be... in the assessment of the effects of these systems on structures. Applicability As discussed...

  7. 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...

  8. 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

    ... protection intended by the airworthiness standards, these non- traditional, large, non-metallic panels in the... with Non-Traditional, Large, Non-Metallic Panels AGENCY: Federal Aviation Administration (FAA), DOT... unusual design feature associated with the airplane seats that have non-traditional, large,...

  9. 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)

  10. 78 FR 58960 - Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-25

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; BAE SYSTEMS... rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This proposed...

  11. 77 FR 20572 - Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-05

    ... Directives; BAE Systems (Operations) Limited Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... (AD) for certain BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 and Model Avro 146-RJ airplanes. This... information identified in this proposed AD, contact BAE SYSTEMS (Operations) Limited, Customer...

  12. 77 FR 3587 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-01-25

    ... new airworthiness directive (AD) for certain Model 767-200 and 767-300 series airplanes. This AD was... potential loss of several functions essential for safe flight. DATES: This AD is effective February 29, 2012...) Applicability This AD applies to The Boeing Company Model 767-200 and 767-300 series airplanes, certificated...

  13. 78 FR 6247 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-30

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; the Boeing Company... Company Model 757 airplanes. The existing AD currently requires revising the maintenance program by..., 2012), for all The Boeing Company Model 757 airplanes. That AD superseded AD 2008-10-11, Amendment...

  14. 78 FR 6254 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-01-30

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; The Boeing Company... directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. That NPRM proposed... all The Boeing Company Model 737-300, -400, and -500 series airplanes. That NPRM published in...

  15. 78 FR 38550 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-27

    ...-226-AD; Amendment 39-17493; AD 2013-13-05] RIN 2120-AA64 Airworthiness Directives; The Boeing Company... 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...

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

    NASA Technical Reports Server (NTRS)

    Dawson, C. R.; Omar, E.

    1977-01-01

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

  17. Free-Spinning-Tunnel Tests of a 1/18-Scale Model of the Fairchild XNQ-1 Airplane, TED No. NACA 2398

    NASA Technical Reports Server (NTRS)

    Daughtridge, Lee T., Jr.

    1946-01-01

    Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/18-scale model of the Fairchild XNQ-1 airplane. The spin and recovery characteristics of the model were determined for the normal gross-weight loading and for two variations from this loading - center of gravity moved rearward and relative mass distribution increased along the fuselage. These tests were performed for two vertical-tail plan forms. The investigation also included simulated pilot-escape tests and rudder-force tests. The recovery characteristics of the model were satisfactory for all conditions tested by full reversal of the rudder and by simultaneous neutralization of the rudder and elevator. It was indicated that if necessary to escape from the spinning airplane, the pilot should jump from the outboard side of the fuselage and as far rearward as possible. Aa determined from spin model tests, the rudder pedal force required to reverse the rudder for recovery from the spin will be light.

  18. 76 FR 53301 - Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-26

    ...-16787; AD 2011-18-05] RIN 2120-AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 2000..., 44701. Sec. 39.13 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2011-18-05 Saab AB...) None. Applicability (c) This AD applies to Saab AB, Saab Aerosystems Model SAAB 2000...

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

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

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

  20. 76 FR 63167 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes With Supplemental Type...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-12

    ...; AD 2011-21-10] RIN 2120-AA64 Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes... directive (AD) for Diamond Aircraft Industries GmbH Model (Diamond) DA 40 airplanes equipped with cabin air... directive (AD): 2011-21-10 Diamond Aircraft Industries GmbH Airplanes Equipped With Supplemental...

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

    ERIC Educational Resources Information Center

    Federal Aviation Administration (DOT), Washington, DC.

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

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

    NASA Technical Reports Server (NTRS)

    Healy, Frederick M.

    1958-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Johnson, Joseph L.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1947-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included tail-modification, spin-recovery parachute, pilot-escape, and rudder-pedal-force tests. Recoveries were generally satisfactory for spins in the normal loading provided the ailerons were not held against the spin. Satisfactory recoveries were obtained regardless of the aileron setting when the leading-edge flaps were deflected and normal recovery technique was used or when the horizontal tail was raised 70 inches, full scale. Recoveries were rapid from all inverted spins obtained. In the long-range loading with tanks on, it may be necessary to jettison the tanks in order to obtain recovery. A 12.0-foot spin-recovery parachute at the tail or a 4.0-foot parachute opened on the outer wing tip (drag coefficient of 0.66) was found to be effective for recoveries from demonstration spins. Test results showed that in an emergency the pilot should attempt to escape from the outboard side of the spinning airplane. The rudder-pedal forces in a spin were indicated to be within the capabilities of the pilot.

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

    NASA Technical Reports Server (NTRS)

    Snyder, Thomas L.

    1947-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Daughtridge, Lee T., Jr.

    1948-01-01

    An investigation of the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics were determined, as were also the effects of extending the wing slats, of center-of-gravity movement, and-of variation in the mass distribution. The investigation also included wing-tip spin-recovery-parachute tests, pilot-escape tests, and rudder-control-force tests. The investigation indicated that the spin and recovery characteristics of the airplane will be satisfactory for all conditions. It was found that a single 4.24-foot (full-scale) parachute when opened alone from the outboard wing tip or two 8.77-foot (full-scale) parachutes when opened simultaneously, one from each wing tip, would effect satisfactory emergency recoveries (the drag coefficients of the parachutes, based on the surface area of the parachute, were 0.83 and 0.70 for the 4.24- and 8.77-foot parachutes, respectively). The towline length in both cases was 25 feet (full scale). Tests results showed that, if the pilot should have to leave the airplane during a spin, he should jump from the outboard side (left side in a right spin) of the cockpit. The rudder-control force necessary for recovery from a spin was found to be rather high but appeared to be within the upper limits of a pilot's capabilities.

  7. Force Characteristics in the Submerged and Planing Condition of a 1/5.78-Scale Model of a Hydro-Ski-Wheel Combination for the Grumman JRF-5 Airplane. TED No. NACA DE 357

    NASA Technical Reports Server (NTRS)

    Land, Norman S.; Pelz, Charles A.

    1952-01-01

    Force characteristics determined from tank tests of a 1/5.78 scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions.

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

    NASA Technical Reports Server (NTRS)

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

    1960-01-01

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

  9. Gordon Bennett Airplane Cup

    NASA Technical Reports Server (NTRS)

    Margoulis, W

    1921-01-01

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

  10. 78 FR 39567 - Airworthiness Directives; Embraer S.A. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-02

    ...-107-AD; Amendment 39-17477; AD 2013-11-17] RIN 2120-AA64 Airworthiness Directives; Embraer S.A... Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. AD 2010-14-14 currently requires, for certain airplanes... bleed system with a new check valve and new seals, replacing the low pressure check valves (LPCVs),...

  11. 78 FR 33193 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-04

    ... hidden parts of the airplane. The FAA made this safety determination based on tests of aged BMS 8-39... (such as the installation of felt on Model 767 airplanes per Figure 18 of Boeing Special Attention... retardant properties, which deteriorate over time, can provide a fuel source for an ignition event in...

  12. 77 FR 71729 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-04

    ...). SUMMARY: We propose to supersede an existing airworthiness directive (AD) that applies to certain Bombardier, Inc. Model DHC-8-400 series airplanes. The existing AD currently requires a free-play check for... PCU. Since we issued that AD, we have determined that additional airplanes are affected by...

  13. 77 FR 15293 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-15

    ... 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 7X airplanes. The existing AD currently requires revising the Abnormal Procedures...

  14. 77 FR 60323 - Airworthiness Directives; DASSUALT AVIATION Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-03

    ...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; DASSUALT AVIATION Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... DASSAULT AVIATION Model MYSTERE-FALCON 50 airplanes. This proposed AD was prompted by a...

  15. 77 FR 44511 - Airworthiness Directives; Alpha Aviation Concept Limited Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-30

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Alpha Aviation Concept Limited Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for Alpha Aviation Concept Limited Model R2160 Airplanes. This proposed AD results from...

  16. 78 FR 69785 - Airworthiness Directives; Slingsby Aviation Ltd. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-21

    ... Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Slingsby Aviation Ltd. Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT... (AD) for Slingsby Aviation Ltd. Model T67M260 airplanes. This proposed AD results from...

  17. 78 FR 61220 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-03

    ...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; Dassault Aviation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This proposed AD was prompted by...

  18. 77 FR 61539 - Airworthiness Directives; DASSAULT AVIATION Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-10

    ...; ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120-AA64 Airworthiness Directives; DASSAULT AVIATION Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of... DASSAULT AVIATION Model FALCON 2000, FALCON 2000EX, MYSTERE- FALCON 900 and FALCON 900EX airplanes; and...

  19. 78 FR 40065 - Airworthiness Directives; Dassault Aviation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-03

    ... 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 7X airplanes. The existing AD currently requires adding an automatic reversion...

  20. 78 FR 24689 - Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-26

    ... From the Federal Register Online via the Government Publishing Office #0; #0;Proposed Rules #0... Directives; PILATUS Aircraft Ltd. Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... airworthiness directive (AD) for all PILATUS Aircraft Ltd. Model PC-7 airplanes. This proposed AD results...

  1. 78 FR 54561 - Airworthiness Directives; Piper Aircraft, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-05

    ... From the Federal Register Online via the Government Publishing Office #0; #0;Rules and Regulations...-17457; AD 2013-10-04] RIN 2120-AA64 Airworthiness Directives; Piper Aircraft, Inc. Airplanes AGENCY... Aircraft, Inc. Models PA-31, PA-31-325, and PA-31-350 airplanes. Table 1 of paragraph (g) lists...

  2. 77 FR 72250 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-05

    ... From the Federal Register Online via the Government Publishing Office ] DEPARTMENT OF... Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Aircraft Company Models 172R and 172S airplanes. This proposed AD was prompted by reports of chafing of...

  3. 77 FR 50054 - Airworthiness Directives; Cessna Aircraft Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-20

    ... From the Federal Register Online via the Government Publishing Office #0; #0;Proposed Rules #0... Directives; Cessna Aircraft Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Cessna Aircraft Company Models 172R and 172S airplanes. This proposed AD was prompted by...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-18

    ... Aircraft, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... all Piper Aircraft, Inc. Models PA-31, PA-31-325, and PA-31-350 airplanes. The existing AD currently... or replacement of parts as necessary. Since we issued that AD, forced landings of aircraft...

  5. 78 FR 22802 - Airworthiness Directives; the Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-17

    ... proposed AD would require replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, this proposed AD would also require installing new relay panels, and removing and installing.... (1) For Model 747-200B, 747-200F, 747-300, and 747SP series airplanes: Replace relays and...

  6. 76 FR 67631 - Airworthiness Directives; Cirrus Design Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-02

    ... Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ] ACTION: Notice of proposed... Corporation (Cirrus) Model SR22T airplanes. This proposed AD was prompted by reports of partial loss of engine... information identified in this proposed AD, contact Cirrus Design Corporation, 4515 Taylor Circle,...

  7. 77 FR 64693 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-23

    ...-17221; AD 2012-21-05] RIN 2120-AA64 Airworthiness Directives; Hawker Beechcraft Corporation Airplanes... airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model G58 airplanes. This AD was prompted by notification from Hawker Beechcraft Corporation that certain affected aircraft were produced...

  8. 77 FR 33083 - Airworthiness Directives; WACO Classic Aircraft Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-05

    ... Aircraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule... Aircraft Corporation Models 2T-1A, 2T-1A-1, and 2T-1A-2 airplanes. This AD requires inspection of the front..., contact WACO Classic Aircraft Corporation; 15955 South Airport Rd., Battle Creek, Michigan...

  9. 77 FR 12757 - Airworthiness Directives; Hawker Beechcraft Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-03-02

    ... Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Beechcraft Corporation Models 58 and G58 airplanes. This proposed AD was prompted by installation of... information identified in this proposed AD, contact Hawker Beechcraft Corporation, B091-A04, 10511 E....

  10. 78 FR 42724 - Airworthiness Directives; Beechcraft Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-17

    ... Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 currently requires..., except Federal holidays. For service information identified in this AD, contact Beechcraft Corporation...

  11. 78 FR 65185 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION... 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 727 airplanes. This AD...

  12. 77 FR 12173 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-29

    .... 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...-2C10 (Regional Jet Series 700, 701, & 702) airplanes; Model CL-600-2D15 (Regional Jet Series...

  13. 78 FR 32579 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-31

    ... 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...-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series...

  14. 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... to read as follows: 2010-17-18 Air Tractor, Inc.: Amendment 39-16412; Docket No. FAA- 2010-0827...) Ensure that the hopper is empty. (3) Limit airspeed to 135 miles per hour (mph) indicated airspeed...

  15. 75 FR 57664 - Airworthiness Directives; G ROB-WERKE Model G120A Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-22

    ...-024-AD; Amendment 39-16435; AD 2010-20-01] RIN 2120-AA64 Airworthiness Directives; G ROB-WERKE Model.... The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113.... (g) You may at any time complete GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April...

  16. 76 FR 12845 - Airworthiness Directives; APEX Aircraft Model CAP 10 B Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-09

    ...-063-AD; Amendment 39-16625; AD 2011-06-01] RIN 2120-AA64 Airworthiness Directives; APEX Aircraft Model... was the improper locking of a turnbuckle (locking clip missing) of the flight control cables, and the... was the improper locking of a turnbuckle (locking clip missing) of the flight control cables, and...

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

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-11

    ... supporting structure. Applicability As discussed above, these special conditions are applicable to the Model...-engine installations, the engine mounts, pylons, and adjacent supporting airframe structure must be... auxiliary power unit (APU) installations, the APU mounts and adjacent supporting airframe structure must...

  18. Low-Speed Longitudinal Stability Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

    NASA Technical Reports Server (NTRS)

    Sleeman, William C.; Byrnes, Andrew L.

    1953-01-01

    A low-speed investigation was made of a 1/6-scale model of the Republic XF-84H airplane. The model had a single tractor propeller and a 40deg swept wing of aspect ratio 3.45. This investigation was undertaken to provide information on the effects of propeller operation on longitudinal stability characteristics for the XF -84H airplane and to provide an indication of slipstream effects that might be encountered on similar swept-wing configurations. Effects of propeller operation were generally destabilizing for all conditions investigated; however, the over-all stability characteristics with power on were greatly dependent on the power-off characteristics. With flaps and slats retracted, longitudinal instability was present at moderate angles of attack both with the propeller off and with power on. The longitudinal stability with flaps and slats deflected, which was satisfactory without power, was decreased by propeller operation, but no marked pitch-up tendency was indicated. Significant improvement in the power-on stability with flaps retracted was achieved by use of either a wing fence at 75 percent semispan, a leading-edge chord-extension from 65 to 94 percent semispan, or a raised horizontal tail located 65 percent semispan above the thrust line.

  19. 76 FR 79560 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-22

    ... ``PRIM 1'' inoperative is prohibited.'' (1) Model A330-223F and -243F airplanes. (2) Model A330-200 and... ``PRIM 1'' inoperative is allowed provided that the operational test of the FCPC3 second electrical power... applicable, before dispatch with FCPC ``PRIM 1'' inoperative.'' Note 3: Model A330-223F and -243F...

  20. Wind tunnel and ground static tests of a .094 scale powered model of a modified T-39 lift/cruise fan V/STOL research airplane

    NASA Technical Reports Server (NTRS)

    Hunt, D.; Clinglan, J.; Salemann, V.; Omar, E.

    1977-01-01

    Ground static and wind tunnel test of a scale model modified T-39 airplane are reported. The configuration in the nose and replacement of the existing nacelles with tilting lift/cruise fans. The model was powered with three 14 cm diameter tip driven turbopowered simulators. Forces and moments were measured by an internal strain guage balance. Engine simulator thrust and mass flow were measured by calibrated pressure and temperature instrumentation mounted downstream of the fans. The low speed handling qualities and general aerodynamic characteristics of the modified T-39 were defined. Test variables include thrust level and thrust balance, forward speed, model pitch and sideslip angle at forward speeds, model pitch, roll, and ground height during static tests, lift/cruise fan tilt angle, flap and aileron deflection angle, and horizonal stabilizer angle. The effects of removing the landing gear, the lift/cruise fans, and the tail surfaces were also investigated.

  1. Low-speed wind-tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on a medium range wide-body tri-jet airplane model

    NASA Technical Reports Server (NTRS)

    Croom, D. R.; Vogler, R. D.; Williams, G. M.

    1976-01-01

    An investigation was made in the V/STOL tunnel to determine, by the trailing wing sensor technique, the effectiveness of various segments of the existing flight spoilers on a medium range wide body tri-jet transport airplane model when they were deflected as trailing vortex alleviation devices. 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 15 to 60 percent at distances behind the transport model of from 3.9 to 19.6 transport wing spans, 19.6 spans being the downstream limit of distances used. Essentially all of the reduction in induced rolling moment on the trailing wing model was realized at a spoiler deflection of about 45 deg.

  2. Quantifying and scaling airplane performance in turbulence

    NASA Astrophysics Data System (ADS)

    Richardson, Johnhenri R.

    This dissertation studies the effects of turbulent wind on airplane airspeed and normal load factor, determining how these effects scale with airplane size and developing envelopes to account for them. The results have applications in design and control of aircraft, especially small scale aircraft, for robustness with respect to turbulence. Using linearized airplane dynamics and the Dryden gust model, this dissertation presents analytical and numerical scaling laws for airplane performance in gusts, safety margins that guarantee, with specified probability, that steady flight can be maintained when stochastic wind gusts act upon an airplane, and envelopes to visualize these safety margins. Presented here for the first time are scaling laws for the phugoid natural frequency, phugoid damping ratio, airspeed variance in turbulence, and flight path angle variance in turbulence. The results show that small aircraft are more susceptible to high frequency gusts, that the phugoid damping ratio does not depend directly on airplane size, that the airspeed and flight path angle variances can be parameterized by the ratio of the phugoid natural frequency to a characteristic turbulence frequency, and that the coefficient of variation of the airspeed decreases with increasing airplane size. Accompanying numerical examples validate the results using eleven different airplanes models, focusing on NASA's hypothetical Boeing 757 analog the Generic Transport Model and its operational 5.5% scale model, the NASA T2. Also presented here for the first time are stationary flight, where the flight state is a stationary random process, and the stationary flight envelope, an adjusted steady flight envelope to visualize safety margins for stationary flight. The dissertation shows that driving the linearized airplane equations of motion with stationary, stochastic gusts results in stationary flight. It also shows how feedback control can enlarge the stationary flight envelope by alleviating

  3. The Bristol "Badminton" Airplane

    NASA Technical Reports Server (NTRS)

    1926-01-01

    The Bristol Badminton, Type 99 airplane has a radial aircooled engine (a Bristol Jupiter 9 cylinder 450 HP.) and three fuel tanks. It is a single seat biplane weighing 1,840 lbs. empty and 2,460 lbs. loaded.

  4. Hovering and Transition Flight Tests of a 1/5-Scale Model of a Jet-Powered Vertical-Attitude VTOL Research Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1961-01-01

    An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/5-scale flying model of a jet-powered vertical-attitude VTOL research airplane in hovering and transition flight. The model was powered with either a hydrogen peroxide rocket motor or a compressed-air jet exhausting through an ejector tube to simulate the turbojet engine of the airplane. The gyroscopic effects of the engine were simulated by a flywheel driven by compressed-air jets. In hovering flight the model was controlled by jet-reaction controls which consisted of a swiveling nozzle on the main jet and a movable nozzle on each wing tip; and in forward flight the model was controlled by elevons and a rudder. If the gyroscopic effects of the jet engine were not represented, the model could be flown satisfactorily in hovering flight without any automatic stabilization devices. When the gyroscopic effects of the jet engine were represented, however, the model could not be controlled without the aid of artificial stabilizing devices because of the gyroscopic coupling of the yawing and pitching motions. The use of pitch and yaw dampers made these motions completely stable and the model could then be controlled very easily. In the transition flight tests, which were performed only with the automatic pitch and yaw dampers operating, it was found that the transition was very easy to perform either with or without the engine gyroscopic effects simulated, although the model had a tendency to fly in a rolled and sideslipped attitude at angles of attack between approximately 25 deg and 45 deg because of static directional instability in this range.

  5. Hovering and Transition Flight Tests of a 1/5-Scale Model of a Jet-Powered Vertical-Attitude VTOL Research Airplane

    NASA Technical Reports Server (NTRS)

    Smith, Charles C., Jr.

    1958-01-01

    An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/5-scale flying model of a jet-powered vertical-attitude VTOL research airplane in hovering and transition flight. The model was powered with either a hydrogen peroxide rocket motor or a compressed-air jet exhausting through an ejector tube to simulate the turbojet engine of the airplane. The gyroscopic effects of the engine were simulated by a flywheel driven by compressed-air jets. In hovering flight the model was controlled by jet-reaction controls which consisted of a swiveling nozzle on the main jet and a movable nozzle on each wing tip; and in forward flight the model was controlled by elevons and a rudder. If the gyroscopic effects of the jet engine were not represented, the model could be flown satisfactorily in hovering flight without any automatic stabilization devices. When the gyroscopic effects of the jet engine were represented, however, the model could not be controlled without the aid of artificial stabilizing devices because of the gyroscopic coupling of the yawing and pitching motions. The use of pitch and yaw dampers made these motions completely stable and the model could then be controlled very easily. In the transition flight tests, which were performed only with the automatic pitch and yaw dampers operating, it was found that the transition was very easy to perform either with or without the engine gyroscopic effects simulated, although the model had a tendency to fly in a rolled and sideslipped attitude at angles of attack between approximately 25 and 45 deg because of static directional instability in this range.

  6. Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction

    NASA Technical Reports Server (NTRS)

    McKinney, Marion O.; Maggin, Bernard

    1944-01-01

    An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed freedom only in yaw. Tests were made with three different amounts of rudder aerodynamic balance and with various values of mass, moment of inertia, and center-of-gravity location of the rudder. Most of the stability derivatives required for the theoretical calculations were determined from forced and free-oscillation tests of the particular model tested. The theoretical analysis showed that the rudder-free motions of an airplane consist largely of two oscillatory modes - a long-period oscillation somewhat similar to the normal rudder-fixed oscillation and a short-period oscillation introduced only when the rudder is set free. It was found possible in the tests to create lateral instability of the rudder-free short-period mode by large values of rudder mass parameters even though the rudder-fixed condition was highly stable. The results of the tests and calculation indicated that for most present-day airplanes having rudders of negative floating tendency, the rudder-free stability characteristics may be examined by simply considering the dynamic lateral stability using the value of the directional-stability parameter Cn(sub p) for the rudder-free condition in the conventional controls-fixed lateral-stability equations. For very large airplanes having relatively high values of the rudder mass parameters with respect to the rudder aerodynamic parameters, however, analysis of the rudder-free stability should be made with the complete equations of motion. Good agreement between

  7. Stall-proof Airplanes

    NASA Technical Reports Server (NTRS)

    Lachmann, G

    1927-01-01

    My lecture has to do with the following questions. Is the danger of stalling necessarily inherent in the airplane in its present form and structure, or can it be diminished or eliminated by suitable means? Do we possess such means or devices and how must they operate? In this connection I will devote special attention to the exhibition of stall-proof airplanes by Fokker under the auspices of the English Air Ministry, which took place in Croyden last April.

  8. 77 FR 9166 - Airworthiness Directives; Airplanes Originally Manufactured by Lockheed for the Military as P2V...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-16

    ... prompted by a report of a significant crack in the principle wing structure on a Neptune Aviation Service... structure on a Neptune Aviation Service, Inc. Model SP-2H (P2V-7) airplane. This condition, if not detected... Aviation, Inc. Model HP-P2V-7 airplanes; (5) Minden Air Corp Model SP-2H (P2V-7) airplanes; (6)...

  9. Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

    NASA Technical Reports Server (NTRS)

    Purser, Paul E.; Spear, Margaret F.

    1947-01-01

    A wind-tunnel investigation has been made to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane model. Although the tests and analyses showed that extreme asymmetry in the horizontal tail indicated a reduction in power effects on longitudinal stability for single-engine single-rotation airplanes, the particular "practical" arrangement tested did not show marked improvement. Differences in average downwash between the normal tail arrangement and various other tail arrangements estimated from computed values of propeller-slipstream rotation agreed with values estimated from pitching-moment test data for the flaps-up condition (low thrust and torque) and disagreed for the flaps-down condition (high thrust and torque). This disagreement indicated the necessity for continued research to determine the characteristics of the slip-stream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement.

  10. Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112

    NASA Technical Reports Server (NTRS)

    Healy, Frederick M.

    1958-01-01

    A supplementary investigation to determine the effect of external fuel tanks on the spin and recovery characteristics of a l/28-scale model of the North American FJ-4 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The model had been extensively tested previously (NACA Research Memorandum SL38A29) and therefore only brief tests were made to evaluate the effect of tank installation. Erect spin tests of the model indicate that flat-type spins-are more prevalent with 200-gallon external fuel tanks than with tanks not installed. The recovery technique determined for spins without tanks, rudder reversal to full against the spin accompanied by simultaneous movement of ailerons to full with the spin, is recommended for spins encountered with external tanks installed. If inverted spins are encountered with external tanks installed, the tanks should be jettisoned and recovery attempted by rudder reversal to full against the spin with ailerons maintained at neutral.

  11. Exhaust-nozzle characterisitcs for a twin-jet variable-wing-sweep fighter airplane model at Mach numbers to 2.2

    NASA Technical Reports Server (NTRS)

    Reubush, D. E.; Mercer, C. E.

    1974-01-01

    A wind-tunnel investigation has been conducted to determine the exhaust-nozzle aerodynamic and propulsive characteristics for a twin-jet variable-wing-sweep fighter airplane model. The powered model was tested in the Langley 16-foot transonic tunnel and in the Langley 4-foot supersonic pressure tunnel at Mach numbers to 2.2 and at angles of attack from about minus 2 to 6 deg. Compressed air was used to simulate the nozzle exhaust flow at values of jet total-pressure ratio from approximately 1 (jet off) to about 21. Effects of configuration variables such as speed-brake deflection, store installation, and boundary-layer thickness on the the nozzle characteristics were also investigated.

  12. Jet Interference Effects on a Model of a Single-Engine Four Jet V/STOL Airplane at Mach Numbers from 0.60 to 1.00

    NASA Technical Reports Server (NTRS)

    Schmeer, James W.; Runckel, Jack F.

    1962-01-01

    An investigation was conducted in the Langley 16-foot transonic tunnel to determine the interference from four exhaust jets on the aerodynamic characteristics of a model of a V/STOL airplane. The single- engine four-jet turbofan power plant of the airplane was simulated by inducing tunnel airflow through two large side inlets and injecting the decomposition products of hydrogen peroxide into the internal flow. The heated gas mixture was exhausted through four nozzles located on the sides of the fuselage under the wing, two near the wing leading edge and two forward of the trailing edge; the nozzles were deflected downward 1.5 deg and outward 5.0 deg to simulate cruise conditions. The wing of the model was a clipped delta with leading-edge sweep of 40 deg, aspect ratio of 3.06, taper ratio of 0.218, thickness-chord ratio of 0.09 at the root and 0.07 at the tip, and 10 deg negative dihedral. Aerodynamic and longitudinal stability coefficients were obtained for the model with the tail removed, and for horizontal-tail incidences of 0 deg and -5 deg. Data were obtained at Mach numbers from 0.60 to 1.00, angles of attack from 0 deg to 12 deg, and with jet total-pressure ratios up to 3.1. Jet operation generally caused a decrease in lift, an increase in pitching-moment coefficient, and a decrease in longitudinal stability at subsonic speeds. The jet interference effects on drag were detrimental at a Mach number of 0.60 and favorable at higher speeds for cruising-flight attitudes.

  13. Effect of Ground Proximity on Aerodynamic Characteristics of Two Horizontal-Attitude Jet Vertical-Take-Off-and-Landing Airplane Models

    NASA Technical Reports Server (NTRS)

    Newsom, William A., Jr.

    1960-01-01

    An investigation has been made to study the effect of ground proximity on the aerodynamic characteristics of two jet vertical-take-off-and-landing airplane models in which the fuselage remains in a horizontal attitude for the take-off and landing. The first model (called the tilt-wing model) had a tilting wing-engine assembly which was set at 90 deg incidence for the take-off and landing. The second model, called the deflected-jet model) had a cascade of retractable turning vanes to deflect the exhaust of the horizontally mounted jet engines downward for vertical take-off and landing while the entire model remained in a horizontal attitude. With the models at various heights above the ground in the take-off and landing configuration, the lift, drag, and pitching moment were measured and tuft surveys were made to determine the flow field caused by the jet exhaust. The tilt-wing model experienced a loss of lift of less than 3 percent near the ground. The deflected-jet model, however, suffered losses in lift as high as 45 percent near the ground because of a low pressure region under the model caused by the entrainment of air by the jet exhaust as it spread out along the ground. This loss in lift for the deflected-jet configuration could probably be reduced to less than 5 percent by the use of a longer landing gear and a high wing location.

  14. Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane in the Langley Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Bennett, Charles V.

    1947-01-01

    An investigation of the low-speed, power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane has been conducted in the Langley free-flight tunnel. In the investigation it was found that with flaps neutral satisfactory flight behavior at low speeds was obtainable with an increase in height of the vertical tail and with the inboard slats opened. In the flap-down slat-open condition the longitudinal stability was satisfactory, but it was impossible to obtain satisfactory lateral-flight characteristics even with the increase in height of the vertical tail because of the negative effective dihedral, low directional stability, and large-adverse yawing moments of the ailerons.

  15. Wind-tunnel investigation of the effect of power and flaps on the static lateral characteristics of a single-engine low-wing airplane model

    NASA Technical Reports Server (NTRS)

    Tamburello, Vito; Weil, Joseph

    1947-01-01

    Tests were made in the Langley 7- by 10-foot tunnel to determine the lateral-stability characteristics with and without power of a model of a typical low-wing single-engine airplane with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. Power decreased the dihedral effect regardless of flap condition, and the double-slotted flap configuration showed the most marked decrease. The usual effect of power in increasing the directional stability was also shown. Deflection of the single slotted flap produced negative dihedral effect, but increased the directional stability. The effects of deflecting the double slotted flap were erratic and marked changes in both effective dihedral and directional stability occurred. The addition of the tail surfaces always contributed directional stability and generally produced positive dihedral effect.

  16. Free-Spinning, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultke MX-813 (Prototype of XP-92) Airplane as Determined in the Langley 20-Foot Free-Spinning Tunnel

    NASA Technical Reports Server (NTRS)

    Stone, Ralph W., Jr.; White, Richard P.

    1948-01-01

    An investigation has been conducted in the Langley 20-foot free-spinning tunnel to evaluate the spin, longitudinal-trim, and tumbling characteristics of a 1/20-scale model of the Consolidated Vultee MX-813 airplane. The effects of control position were determined for the model ballasted to represent the airplane in its design gross weight loading. The model, in general, would not spin but demonstrated a tendency to trim at very high stalled angles of attack. Static tests substantiated the dynamic tests as regards the trim characteristics. Movement of the elevator, however, from up to slightly down was effective in pitching the model from stalled to normal trim attitudes. The model would not tumble.

  17. 77 FR 36146 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-18

    ...-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing... Sensor- Amplifier (FLSA) and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been... sensor-amplifier and multi-tank indicator (MTI) units. We are issuing this AD to prevent degradation...

  18. 78 FR 65187 - Airworthiness Directives; Airbus Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ... and Model A340-200 and -300 series airplanes. This AD was prompted by reports of corrosion found on... the tie bar and the screw-jack. This AD requires repetitive detailed inspections for corrosion of... or new and improved THSA, if necessary. We are issuing this AD to detect and correct corrosion of...

  19. 14 CFR 36.7 - Acoustical change: Transport category large airplanes and jet airplanes.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... airplanes and jet airplanes. 36.7 Section 36.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... § 36.7 Acoustical change: Transport category large airplanes and jet airplanes. (a) Applicability. This section applies to all transport category large airplanes and jet airplanes for which an acoustical...

  20. 14 CFR 36.7 - Acoustical change: Transport category large airplanes and jet airplanes.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... airplanes and jet airplanes. 36.7 Section 36.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... § 36.7 Acoustical change: Transport category large airplanes and jet airplanes. (a) Applicability. This section applies to all transport category large airplanes and jet airplanes for which an acoustical...

  1. 14 CFR 36.7 - Acoustical change: Transport category large airplanes and jet airplanes.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... airplanes and jet airplanes. 36.7 Section 36.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... § 36.7 Acoustical change: Transport category large airplanes and jet airplanes. (a) Applicability. This section applies to all transport category large airplanes and jet airplanes for which an acoustical...

  2. Longitudinal Aerodynamic Modeling of the Adaptive Compliant Trailing Edge Flaps on a GIII Airplane and Comparisons to Flight Data

    NASA Technical Reports Server (NTRS)

    Smith, Mark S.; Bui, Trong T.; Garcia, Christian A.; Cumming, Stephen B.

    2016-01-01

    A pair of compliant trailing edge flaps was flown on a modified GIII airplane. Prior to flight test, multiple analysis tools of various levels of complexity were used to predict the aerodynamic effects of the flaps. Vortex lattice, full potential flow, and full Navier-Stokes aerodynamic analysis software programs were used for prediction, in addition to another program that used empirical data. After the flight-test series, lift and pitching moment coefficient increments due to the flaps were estimated from flight data and compared to the results of the predictive tools. The predicted lift increments matched flight data well for all predictive tools for small flap deflections. All tools over-predicted lift increments for large flap deflections. The potential flow and Navier-Stokes programs predicted pitching moment coefficient increments better than the other tools.

  3. 77 FR 63215 - Airworthiness Directives; Bombardier, Inc. Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-10-16

    .... Model DHC-8-400 series airplanes. That AD currently requires a modification to trim the edge of the... developed a modification to trim the edge of the bumper plate to eliminate the possibility of...

  4. 78 FR 52870 - Airworthiness Directives; Beechcraft Corporation Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-27

    ... Directives; Beechcraft Corporation Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION... certain Beechcraft Corporation (type certificate previously held by Hawker Beechcraft Corporation) Models... identified in this proposed AD, contact Beechcraft Corporation at address: 10511 E. Central, Wichita,...

  5. 75 FR 7942 - Airworthiness Directives; Airbus Model A310-203, -221, -222 Airplanes; and Model A300 F4-605R and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-23

    ... INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane... of Additional Change We have specified the issue numbers of each Airbus operations engineering... missing or damaged, the instructions contained in Airbus A310 Operations Engineering Bulletin 160, Issue...

  6. The evolution of airplanes

    NASA Astrophysics Data System (ADS)

    Bejan, A.; Charles, J. D.; Lorente, S.

    2014-07-01

    The prevailing view is that we cannot witness biological evolution because it occurred on a time scale immensely greater than our lifetime. Here, we show that we can witness evolution in our lifetime by watching the evolution of the flying human-and-machine species: the airplane. We document this evolution, and we also predict it based on a physics principle: the constructal law. We show that the airplanes must obey theoretical allometric rules that unite them with the birds and other animals. For example, the larger airplanes are faster, more efficient as vehicles, and have greater range. The engine mass is proportional to the body size: this scaling is analogous to animal design, where the mass of the motive organs (muscle, heart, lung) is proportional to the body size. Large or small, airplanes exhibit a proportionality between wing span and fuselage length, and between fuel load and body size. The animal-design counterparts of these features are evident. The view that emerges is that the evolution phenomenon is broader than biological evolution. The evolution of technology, river basins, and animal design is one phenomenon, and it belongs in physics.

  7. Longitudinal balancing of airplanes

    NASA Technical Reports Server (NTRS)

    Eteve, Albert

    1923-01-01

    The object of the present communication is to determine the best method for locating the center of lift of an airplane and to provide a method for making corrections. The method employed is very simple, being based on the positions given the elevator during flights at different speeds.

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

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1947-01-01

    An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included leading-edge-flap, spin-recovery-parachute, and rudder-pedal-force tests. The recovery characteristics of the model were satisfactory for the normal loading. Deflecting the leading-edge flaps improved recoveries. The results indicated that with the external wing tanks installed (long-range loading) recoveries may be poor and, therefore, if a spin is inadvertently entered in this condition the tanks should be jettisoned if recovery does not appear imminent immediately after it is attempted. A 10-foot spin-recovery tail parachute with a towline 40 feet long and a drag coefficient of 0.63 was found to be effective for spin recovery. The rudder pedal force required for spin recovery was indicated to be within the capabilities of the pilot.

  9. Free-spinning-tunnel Tests of a 1/26th Scale Model of the Douglas XTB2D-1 Airplane

    NASA Technical Reports Server (NTRS)

    Stone, Ralph W; Berman, Theodore

    1946-01-01

    A spin-tunnel investigation of a 1/26 scale model of the Douglas XTB2D-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements upon the erect- and inverted-spin and recovery characteristics of the model were determined for various loading conditions. Tests were also performed to determine the effects of various tail modifications. The investigation included emergency spin-recovery parachute tests as well as crew-escape and rudder- and elevator-force tests. All tests were performed at an equivalent spin altitute of 20,000 feet. The recovery characteristics of the model in the original design were found to be unsatisfactory. Installation of a large ventral fin, installation of tip fins on the horizontal tail, or installation of a small ventral fin in combination with antispan fillets and a spanwise extension of the horizontal-tail surfaces satisfactorily improved the recovery characteristics of the model.

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

    NASA Technical Reports Server (NTRS)

    Berman, Theodore

    1948-01-01

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

  11. Preliminary Evaluation of the Low-Speed Stability and Control Characteristics of the McDonnell XP-85 Airplane from Tests of an Unballasted 1/5-Scale Model in the Langley Free-Flight Tunnel

    NASA Technical Reports Server (NTRS)

    Paulson, John W.; Johnson, Joseph L.

    1947-01-01

    At the request of the Air Material Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a jet propelled, parasite fighter with a 34 deg sweepback at the wing quarter chord. It was designed to be carried in a bomb bay of the B-36 air plane. The first portion of the investigation consists of a preliminary evaluation of the stability and control characteristics of the airplane from force and fight tests of an unballasted 1/5-scale model. The second portion of the investigation consists of test of a properly balasted 1/10-scale model which will include a study of the stability of the Xp-85 when attached to the trapeze for retraction into the B-36 bomb bay. The results of the preliminary test with the 1/5-scale model are presented herein. This portion fo the investigation included tests of the model with various center fin arrangements. Both the design nose flap and a stall control vane were investigated.

  12. 76 FR 38069 - Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    ..., -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category; equipped with carbon fiber reinforced plastic rudders having any part number and serial number listed in Table 1, 2, 3, or...

  13. Development of a Composite Tailoring Technique for Airplane Wing

    NASA Technical Reports Server (NTRS)

    Chattopadhyay, Aditi; Jha, Ratneshwar

    1996-01-01

    Development of a new composite beam modeling technique to represent the principal load-carrying member in the wing is reported along with the development of a formal design optimization procedure to investigate the effect of composite tailoring on aeroelastic stability and structural characteristics of airplane wings. The developed procedure is used to perform design optimization studies on realistic airplane configurations to investigate the various aeroelastic/structural/dynamic design issues.

  14. Supplemental data and calculations of the lateral stability of airplanes

    NASA Technical Reports Server (NTRS)

    Mathias, Gotthold

    1934-01-01

    In connection with the DVL Report 272 on the theory of the lateral stability of airplanes, the formal results are here amplified in some respects and their technical significance again briefly explained. Three numerical examples show how model tests for checking the lateral stability are to be evaluated and supplemented, if necessary, and how the stability limits depend on the design of the airplane and on the conditions of flight.

  15. Low-speed aerodynamic characteristics of a 1/8-scale X-29A airplane model at high angles of attack and sideslip

    NASA Technical Reports Server (NTRS)

    Whipple, R. D.; Ricket, J. L.

    1986-01-01

    A 1/8-scale model of the X-29A airplane was tested in the Ames 12-Foot Pressure Wind Tunnel at a Mach number of 0.20 and Reynolds numbers of 0.13 x 10 to the 6th power to 2.00 x 10 to the 6th power based on a fuselage forebody depth of 0.4 ft, For the test series presented herein, the angle of attack ranged from 40 deg. to 90 deg. and the angle of sideslip ranged from -10 deg. to 30 deg. for the erect attitude. Tests with the model inverted covered angles of attack from -40 deg. to -90 deg. and angles of sideslip from -30 deg. to 10 deg. Data were obtained for the basic design and for several forebody strakes. An alternate forebody design was also tested. The results provided information for selection of forebody strakes for compensation of Reynolds number effect on the 1/25-scale free-spinning model tested in the Langley Spin Tunnel.

  16. Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-tail Component Drag of a Twin-engine Fighter-type Airplane Model

    NASA Technical Reports Server (NTRS)

    Foss, Willard E , Jr; Runckel, Jack F; Lee, Edwin E , Jr

    1958-01-01

    An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the fuselage-tail configurations are presented at Mach numbers from 0.80 to 1.05 angles of attack of 0 degree and 4 degrees for jet pressure ratios from 1 to 7. The effect of jet operation on both the basic and modified models was generally to decrease base pressures but to increase most other afterbody pressures and, therefore, to result in an overall decrease in fuselage-tail component drag. The addition of volume to the basic model reduced the base drag coefficient by 0.0010 with the jets off and 0.0018 at a typical cruise operating condition of a jet pressure ratio of 3, a Mach number of 0.85, and an angle of attack of 4 degrees. The overall jet-off reduction in fuselage-tail component drag due to the volume addition was a maximum of 0.0040 at a Mach number of 0.90 for an angle of attack of 4 degrees.

  17. Summary of spin technology as related to light general-aviation airplanes

    NASA Technical Reports Server (NTRS)

    Bowman, J. S., Jr.

    1971-01-01

    A summary was made of all NASA (and NACA) research and experience related to the spin and recovery characteristics of light personal-owner-type general-aviation airplanes. Very little of the research deals with light general-aviation airplanes as such, but many of the airplanes and models tested before and during World War II were similar to present-day light general-aviation airplanes with regard to the factors that are important in spinning. The material is based mainly on the results of spin-tunnel tests of free-spinning dynamically scaled models of about 100 different airplane designs and, whenever possible, includes correlation with full-scale spin tests. The research results are discussed in terms of airplane design considerations and the proper use of controls for recovery.

  18. Exploring Venus by Solar Airplane

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.

    2001-01-01

    A solar-powered airplane is proposed to explore the atmospheric environment of Venus. Venus has several advantages for a solar airplane. At the top of the cloud level, the solar intensity is comparable to or greater than terrestrial solar intensities. The Earthlike atmospheric pressure means that the power required for flight is lower for Venus than that of Mars, and the slow rotation of Venus allows an airplane to be designed for continuous sunlight, with no energy storage needed for night-time flight. These factors mean that Venus is perhaps the easiest planet in the solar system for flight of a long-duration solar airplane.

  19. Wind-Tunnel Investigation of Some Effects of Wing Sweep and Horizontal-Tail Height on the Static Stability of an Airplane Model at Transonic Speeds

    NASA Technical Reports Server (NTRS)

    Fisher, Lewis R.; Williams, James L.

    1958-01-01

    A research model of an airplane with a configuration suitable for supersonic flight was tested at transonic speeds in order to establish the effects on longitudinal and lateral stability of certain changes in both wing sweep and height of the horizontal tail. Two wings of aspect ratio 3 and taper ratio 0.15, one having the quarter-chord line swept back 30 deg and the other 45 deg, were each tested with the horizontal tail of the model in a low and in a high position. One configuration was also tested with fuselage strakes. The tests were made at Mach numbers from 0.60 to 1.17 and Reynolds numbers from 1.9 x 10(exp 6) to 2.6 x 10(exp 6). The results indicated that a low horizontal-tail position (below the wing-chord plane) gave positive longitudinal stability for the model for all angles of attack used (angles of attack up to 24 deg); whereas, a higher tail position (above the wing-chord plane) resulted in a large reduction in stability at moderate angles of attack. With the higher horizontal tail, the 30 deg-swept-wing model had somewhat more stability than the 45 deg-swept-wing model at subsonic Mach numbers. With the lower tail, the 45 deg-swept-wing model had slightly more stability at all Mach numbers. The model with the 30 deg swept wing had greater directional stability with the tail in the higher rather than the lower position, but the opposite was true for the 45 deg-swept-wing model. The directional stability decreased sharply at high angles of attack; this characteristic was alleviated by the use of fuselage strakes which, however, proved to be detrimental to the longitudinal stability of the model tested.

  20. 75 FR 61989 - Airworthiness Directives; McDonnell Douglas Corporation Model DC-8-31, DC-8-32, DC-8-33, DC-8-41...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-07

    ... Corporation Model DC- 8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8-50 Series Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-60 Series Airplanes; Model DC-8-60F Series Airplanes; Model DC-8- 70 Series Airplanes; and Model DC-8-70F Series Airplanes AGENCY:......