Preliminary Airworthiness Evaluation Of The Uh 60 Helicopter With T700 Ge 701a Engines Installed PDF Download
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| Author | : J. I. Nagata |
| Publisher | : |
| Total Pages | : 45 |
| Release | : 1983 |
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Download Preliminary Airworthiness Evaluation of the UH-60 Helicopter with T700-GE-701A Engines Installed Book in PDF, ePub and Kindle
This limited preliminary evaluation, conducted 24-25 June 1983, consisted of three flights for a total of 4.8 productive flight hours. The significant increase in power available for single engine contingencies (262 shaft horsepower (22%) at 4000 ft pressure altitude, 95 F) is an enhancing characteristic. The excellent torque matching engine stability and rotor speed control with one engine in electrical control unit lockout and the power lever set for level flight at 80 knots indicated airspeed is also an enhancing characteristic for both the T700-GE-701A engine and T700-GE-700 engine. The UH-60A acceleration, deceleration, and normal maneuvering response characteristics are essentially the same with either the T700-GE-700 engine or T700-GE-701A engine installed. Two shortcomings were identified: (1) slow engine acceleration during collective pulls from approximately zero torque to 50% or greater torque; and (2) rotor droop to less than 95% rotor speed during collective pulls from zero torque and during aggressive maneuvers such as a quick stop from the maximum airspeed in level flight. During the evaluation a popping sound was noted during collective pulls to approximately 80% and greater torque settings. This popping sound was subsequently identified as oil canning on the fuselage skin between the pilot's station and gunner/crew chief's window.
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| Total Pages | : 56 |
| Release | : 1989 |
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Download Preliminary Airworthiness Evaluation of the Woodward Hydromechanical Unit Installed on T700-GE-700 Engines in the UH-60A Helicopter Book in PDF, ePub and Kindle
The U.S. Army Aviation Engineering Flight Activity conducted a Prelimiary Airworthiness Evaluation of the Woodward Hydromechanical Unit (HMU) installed on T700-GE-700 engines in the UH-60A helicopter from 14 May 1989 to 14 June 1989. The evaluation was conducted at Edwards AFB, California (elevation 2302 feet) and Coyote Flat, California (elevation 9980 feet) on aircraft S/N 88- 26015. The evaluation consisted of eleven flights for a total of 15.5 productive flight hours. Performance of the Woodward HMU and the Hamilton Standard HMU, presently used on T700-GE-700 engines, was similar. The poor engine/rotor transient droop characteristics, as noted in previous testing, remain a shortcoming regardless of the HMU installed. Operation of T700-GE-700 engines with Woodard HMUs installed is satisfactory.
| Author | : |
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| Total Pages | : 964 |
| Release | : 1988 |
| Genre | : Aeronautics |
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Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
| Author | : Charles E. Cassil |
| Publisher | : |
| Total Pages | : 97 |
| Release | : 1986 |
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Download Preliminary Airworthiness Evaluation of the UH-1H Helicopter with the T53-L-703 Engine Installed Book in PDF, ePub and Kindle
Performance, handling qualities, and overall engine-airframe compatibility were evaluated to substantiate an airworthiness release and appropriate restrictions in the operator's manual. These tests were conducted at Bakersfield, Edwards AFB, Bishop, and Coyote Flats, California. Thirty-four flights were conducted for a total of 26.3 productive flight hours. the performance, handling qualities, and overall engine-airframe compatibility of the aircraft with the T53-L-13B engine are unchanged from those with the T53-L-13B engine when the aircraft is operated within the power-available capability of the -13B. Two shortcomings were identified: (1) poor torque gauge readability, and (2) ignition key location. Engine exhaust impingement on the tail boom produced skin temperatures high enough to cause loss of tail boom structural strength. No engine installation or maintenance problems were encountered during the evaluation.
| Author | : M. L. Hanks |
| Publisher | : |
| Total Pages | : 158 |
| Release | : 1983 |
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Download Preliminary Airworthiness Evaluation of UH-60A with an Improved Airspeed System Book in PDF, ePub and Kindle
The United States Army Aviation Engineering Flight Activity supported a contractor engineering effort to correct the nose-down pitch-over during takeoff and the large, variable position error in the low-speed flight regime of the UH-60A (Black Hawk) helicopter. A Preliminary Airworthiness Evaluation was then conducted with the improved airspeed and stabilator systems in their final configuration as defined by the contractor. Handling qualities and airspeed system characteristics were evaluated for two modified overhead and one nose probe configuration. In addition, airspeed system tests were conducted on a second nose probe configuration. Four shortcomings applicable to the modified overhead probe systems were identified as follows: (1) the annoying longitudinal control, stabilator angle, and indicated airspeed reversals resulting in pitch attitude oscillations during takeoff (upgraded from a deficiency in the standard production aircraft); (2) the high pilot workload required to maintain precise airspeed during transitions to high power, low airspeed climbs; (3) the large, variable airspeed position errors; and (4) unreliable airspeed indications in low airspeed, high power climbs. For the modified overhead probe systems the following should be accomplished: (1) evaluate the proposed installation on the External Stores Support System UH-60 helicopter, and (2) evaluate the proposed installation on an extremely light gross weight UH-60 helicopter.
| Author | : Michael K. Herbst |
| Publisher | : |
| Total Pages | : 114 |
| Release | : 1988 |
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Download Preliminary Airworthiness Evaluation of the UH-60A External Fuel System Book in PDF, ePub and Kindle
Testing was conducted to determine the effects of the installation of the External Fuel System (EFS) on the performance and handling qualities of the UH-60A helicopter. A total of 27 productive flight hours were flown at Edwards Air Force Base, California between 21 March and 20 May 1988. The evaluation did not reveal any problems that should preclude airworthiness qualification. The installation of the EFS with two 230-gallon tanks caused an increase in power required to hover in ground effect (10-foot wheel height) and out of ground effect of approximately 5 percent and 6 percent, respectively. The change in equivalent flat plate area in the EFS configuration with two 230-gallon tanks varied from 6.2 to 12.4 square feet when compared to the UH-60A in the normal utility configuration. The drag of the UH-60A in the EFS configuration with two 230-gallon tanks is significantly increased when the cargo doors and gunner windows are open. Three shortcomings and two Prime Item Development Specification noncompliances were identified during the handling qualities evaluation of the UH-60A in the EFS configuration. Two of the shortcomings have been noted during previous evaluations of the UH-60A in the normal utility configuration. Handling qualities were not significantly different than those of the UH-60A in the normal utility configuration. Keywords: External fuel tanks; Helicopters; Aerodynamics; External fuel system, UH-60A helicopter. (kt).
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| Total Pages | : 83 |
| Release | : 2004 |
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Download Preliminary Airworthiness Evaluation of an Engine Inlet Barrier Filter on a UH-60A Helicopter Book in PDF, ePub and Kindle
| Author | : United States. Defense Logistics Studies Information Exchange |
| Publisher | : |
| Total Pages | : 1086 |
| Release | : 1985 |
| Genre | : Military research |
| ISBN | : |
Download Annual Department of Defense Bibliography of Logistics Studies and Related Documents Book in PDF, ePub and Kindle
| Author | : Vernon L. Diekmann |
| Publisher | : |
| Total Pages | : 187 |
| Release | : 1978 |
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Download Preliminary Airworthiness Evaluation: UH-1H Helicopter Equipped with Multiple Target Electronic Warfare System (MULTEWS) Book in PDF, ePub and Kindle
The United States Army Aviation Engineering Flight Activity conducted a Preliminary Airworthiness Evaluation (PAE) of a UH-1H helicopter equipped with a Multiple Target Electronic Warfare System (MULTEWS) from 13 August through 2 December 1977. The evaluation was conducted at Edwards Air Force Base, California, and required 45 flights for a total productive flight time of 41 hours. The test program was terminated when the test aircraft sustained major damage during height-velocity testing. The addition of the MULTEWS equipment to the UH-1H airframe caused significant degradation in performance and handling qualities. Changes in the operator's manual should be made to reflect the changes in performance for MULTEWS configured aircraft. The MULTEWS installation also generally degraded the vibration characteristics of the UH-1H, increased structural loads, increased the maintenance workload, and degraded aircraft crashworthiness. The degradation in performance and handling qualities as well as the excessive vibrations and structural loads in the MULTEWS configured aircraft were attributed to the extremely high drag and turbulent wake of the externally mounted MULTEWS components.
| Author | : Arthur R. Marshall |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1983 |
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Download Preliminary Airworthiness Evaluation of the UH-60A Configured with the External Stores Support System (ESSS). Book in PDF, ePub and Kindle
The Preliminary Airworthiness Evaluation of the UH-60A helicopter configured with the External Stores Support System was conducted. A total of 26 test flights were conducted. Limited level flight performance tests were conducted to determine the change in drag of the UH-60A helicopter caused by three External Stores Support System configurations with various stores installed. An unexplained increase in power required was found between the Preliminary Airworthiness Evaluation test aircraft and the aircraft used during a previous Airworthiness and Flight Characteristics evaluation.
