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Instrument Flight Evaluation Oh 58a Helicopter
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Book Synopsis Instrument Flight Evaluation OH-58A Helicopter by : John R. Smith
Download or read book Instrument Flight Evaluation OH-58A Helicopter written by John R. Smith and published by . This book was released on 1972 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The OH-58A light observation helicopter has a single main rotor and a two-bladed, semirigid, and teetering antitorque tail rotor. The tail rotor also has a delta-three hinge. The cockpit provides side-by-side seating for a crew of two (pilot and copilot/observer), and the cargo compartment has seats for two passengers. Dual flight controls are provided. The cyclic and collective controls are hydraulically boosted and irreversible, while the tail rotor control is unboosted. The landing gear consists of fixed, energy-absorbing skids. The helicopter is powered by an Allison T63-A-700 free gas turbine engine with a takeoff power rating of 317 shaft horsepower (shp) under sea-level, standard-day uninstalled conditions. The main transmission has a rating of 270 shp for continuous operation, with a takeoff power limit of 317 shp (5-minute rating). A list of the aircraft flight instruments and navigation equipment is shown.
Book Synopsis Handling Qualities Evaluation of the OH-58A Helicopter Incorporating the Model 570B Three-axis Stability and Control Augumentation System by : Raymond B. Smith
Download or read book Handling Qualities Evaluation of the OH-58A Helicopter Incorporating the Model 570B Three-axis Stability and Control Augumentation System written by Raymond B. Smith and published by . This book was released on 1973 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited handling qualities evaluation of the OH-58A helicopter with a Bell Helicopter Model 570B three-axis stability and control augmentation system installed was conducted to determine its capability to perform instrument flight. Testing was performed by the US Army Aviation Systems Test Activity at Edwards Air Force Base, California. The testing consisted of 25 productive flight hours and was conducted from September through November 1972. The evaluation revealed significant improvements in the aircraft handling qualities with the addition of the augmentation system. The most significant enhancing characteristics provided by the equipment were: (1) increased damping of the lateral-directional oscillation (Dutch roll), (2) improvement of aircraft spiral stability from neutral to convergent, and (3) reduction in pilot effort required to maintain trim flight conditions. This evaluation was of limited scope, and primarily addressed handling qualities. It did not provide a basis to qualify the aircraft for instrument flight.
Book Synopsis Flight Test Guide by : United States. Flight Standards Service
Download or read book Flight Test Guide written by United States. Flight Standards Service and published by . This book was released on 1977 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Instrument Rating (helicopter) Written Test Guide by : United States. Federal Aviation Administration
Download or read book Instrument Rating (helicopter) Written Test Guide written by United States. Federal Aviation Administration and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Evaluation: MK II Integrated Controller Installed in an OH-58 Helicopter by : John F. Hagen
Download or read book Flight Evaluation: MK II Integrated Controller Installed in an OH-58 Helicopter written by John F. Hagen and published by . This book was released on 1978 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: This Activity conducted a limited handling qualities and pilot workload evaluation of the MK II integrated controller installed in an OH-58A helicopter. The evaluation consisted of 22 flights for 15.2 hours of productive flight test time. The OH-58A could be safely flown throughout the recommended flight envelope using the integrated controller. The pilot workload when using the integrated controller with two hands was not reduced from and was sometimes greater than the workload when using conventional controls for all maneuvers except level forward flight. Single hand control during flight and landing could be safely accomplished, but required increased pilot workload in all cases. The two most serious unsatisfactory characteristics identified were lack of an adequate system-decoupled warning and excessive workload during left sideward flight between approximately 15 to 25 knots true airspeed. Three unsatisfactory characteristics that contributed to the increased workload when using the integrated controller were excessive longitudinal and lateral integrated controller response and sensitivity, lack of control displacement harmony between the integrated controller cyclic and collective controls, and inadvertent cyclic control inputs with collective control movement. The reduced longitudinal and lateral control authority, which limited the aircraft's forward flight capability at aft center of gravity, rearward flight capability at forward center of gravity, and slope landing capability, was also an unsatisfactory characteristic. Eight additional unsatisfactory characteristics were also identified.
Download or read book Operator's Manual written by and published by . This book was released on 1989 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Instrument Flight-Evaluation OH-6A Helicopter by : Albert L. Winn
Download or read book Instrument Flight-Evaluation OH-6A Helicopter written by Albert L. Winn and published by . This book was released on 1973 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited flying qualities and operational performance evaluation was conducted on the OH-6A helicopter to determine the suitability for operation under instrument flight conditions. The operational evaluation was performed with and without a Kaiser FP-50B flight director system installed. Tests were conducted at the United States Army Aviation Systems Test Activity, Edwards Air Force Base, California, during the period from February 1972 to August 1973. (Modified author abstract).
Book Synopsis Evaluation of an OH-58A Helicopter with an Allison 250-C20B Engine by : Tom P. Benson
Download or read book Evaluation of an OH-58A Helicopter with an Allison 250-C20B Engine written by Tom P. Benson and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Instructor Instrument Rotorcraft-helicopter Written Test Guide by : United States. Flight Standards Service
Download or read book Flight Instructor Instrument Rotorcraft-helicopter Written Test Guide written by United States. Flight Standards Service and published by . This book was released on 1977 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluations of Helicopter Instrument-flight Handling Qualities by : S. R. M. Sinclair
Download or read book Evaluations of Helicopter Instrument-flight Handling Qualities written by S. R. M. Sinclair and published by . This book was released on 1982 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Instrument Panel and Avionics Compartment Environmental Survey Production OH-58A Helicopter by : Emmett J. Lang
Download or read book Instrument Panel and Avionics Compartment Environmental Survey Production OH-58A Helicopter written by Emmett J. Lang and published by . This book was released on 1972 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: Vibration and temperature measurement tests were conducted on a production OH-58A helicopter to define the instrument and avionics vibration and temperature environment for both weapons-firing and nonweapons-firing flight conditions. Testing was performed by the United States Army Aviation Systems Test Activity, Edwards Air Force Base, California, between 27 May and 24 June 1971. The testing consisted of four flights, totaling 3.0 productive test hours. Vibration data were recorded from seven triaxial accelerometer locations for 29 flight conditions, and narrow-band spectral analyses were performed on the vibration data. The results of the spectral analyses were summarized by use of statistical methods. The primary source of low-frequency vibrations was the main rotor, and the primary source of high-frequency vibrations was gunfire. The characteristic of the instrument and avionics vibration isolation mounts to amplify the vibrations at the main rotor driving frequencies is a short coming. Interior cabin temperatures of 25 C and 6 C above the ambient air temperature were recorded for static and in-flight conditions, respectively. (Author).
Book Synopsis Survey of Helicopter Control/display Investigations for Instrument Decelerating Approach by :
Download or read book Survey of Helicopter Control/display Investigations for Instrument Decelerating Approach written by and published by . This book was released on 1979 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis OH-58A Autorotational Evaluation by : Joseph C. Watts
Download or read book OH-58A Autorotational Evaluation written by Joseph C. Watts and published by . This book was released on 1972 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several recent instances of tail-boom buckling have occurred after an autorotational touchdown in the OH-58A helicopter. These occurrences prompted the US Army Aviation System Command (AVSCOM) light observation helicopter (LOH) Project Manager to enter into a product improvement program (PIP) with Bell Helicopter Company (BHC) to define the problem and recommend a solution. This PIP task included computer studies, a shake test, and flight testing of a structurally instrumented OH-58A helicopter. The results of the PIP task, to date, indicate that the tail-boom buckling resulted from a resonant condition between the main rotor and the natural frequencies of the fore and aft pylon mode and the tail boom. This resonant frequency, 5 hertz, was likely to occur at high blade angles (100-percent collective) and low rotor speed (150 rpm) and was associated with large main rotor flapping excursions. Three solutions were considered: (1) change the natural frequencies of the fore and aft pylon mode and/or tail boom, (2) damp the pylon movement, and (3) eliminate the excessive blade flapping. The BHC chose the third solution by electing to restrict the maximum collective control travel which would, in turn, eliminate excessive flapping at low rotor speeds. The BHC testing showed that there was no degradation of helicopter performance as the result of the installation of an 80-percent collective pitch restriction device.
Book Synopsis Airworthiness and Flight Characteristics Evaluation. OH-58C Interim Scout Helicopter by :
Download or read book Airworthiness and Flight Characteristics Evaluation. OH-58C Interim Scout Helicopter written by and published by . This book was released on 1979 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Activity conducted an airworthiness and flight characteristics evaluation of the OH-58C Interim Scout helicopter. Performance, handling qualities, and vibration characteristics were evaluated to provide engineering test data for use in the OH-58C Operator's Manual and to detect any aircraft deficiencies or shortcomings. The OH-58C was tested at Edwards Air Force Base, California (elevation 2302 feet), and alternate test site elevations of 4120, and 9980 feet. A total of 97 flights were conducted for a total of 123.5 flight hours. Due to the more powerful T63- A-720 engine installed in the helicopter, the hover and takeoff capability at heavy gross weights and high altitudes and the forward flight climb performance of the OH-58C is significantly improved over the OH-58A. Performance in terms of power required and fuel flow is slightly degraded when compared to the OH-58A at similar gross weights and altitudes and in general did not meet the estimates of the detail specification for the OH-58C. The handling qualities and vibrations of the OH-58C are similar to the OH-58A when operating at similar gross weights and altitudes. Three handling qualities deficiencies relative to the low speed flight characteristics were identified.
Book Synopsis Engineering Evaluation JOH-58A Helicopter with an Automatic Relight System by : Tom P. Benson
Download or read book Engineering Evaluation JOH-58A Helicopter with an Automatic Relight System written by Tom P. Benson and published by . This book was released on 1975 with total page 83 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a limited in-flight evaluation of an automatic engine relight system installed in an OH-58A helicopter at Edwards Air Force Base, California, from 12 February through 11 April 1975. During the program, 33 test flights were flown for a total of 13.5 productive flight hours. Results of the evaluation showed that established limitations may be exceeded if the automatic relight system functions at certain points within the current operating envelope. Required additional limitations to the current operating envelope with the automatic relight system activated include in-ground-effect, hover below 10 feet and specific combinations of airspeeds and engine power settings. Two deficiencies and one shortcoming were noted during the evaluation.
Book Synopsis Instrument Flying for Helicopter Aircraft by : United States. Department of the Air Force
Download or read book Instrument Flying for Helicopter Aircraft written by United States. Department of the Air Force and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
