Airworthiness And Flight Characteristics Evaluation Uh 60a Black Hawk Helicopter PDF Download
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| Author | : John I. Nagata |
| Publisher | : |
| Total Pages | : 267 |
| Release | : 1981 |
| Genre | : |
| ISBN | : |
Download Airworthiness and Flight Characteristics Evaluation, UH-60A (Black Hawk) Helicopter Book in PDF, ePub and Kindle
The United States Army Aviation Engineering Flight Activity conducted an Airworthiness and Flight Characteristics Evaluation of the third and fourth production UH-60A (Black Hawk) helicopters from 27 October 1979 through 9 October 1980. Performance, handling qualities, and vibration characteristics were evaluated to provide data for the operator's manual and to determine compliance with the applicable paragraphs of the Prime Item Development Specification. The UH-60A met 5 of the 7 performance comments evaluated with reference to the Prime Item Development Specification. The performance of the UH-60A was better than the YUH-60A because of the lower primary mission gross weight of the aircraft, the reduced power required, and the increased power available. Due to the priorities set by United States Army Aviation Research and Development Command the handling qualities portion of the Airworthiness and Flight Characteristics Evaluation was extremely limited. The excellent engine torque matching greatly reduced pilot work load in the area of power management. When maneuvering, the limited load factor envelope at heavy gross weight was easily exceeded. The vibrations were found to be quite high in several areas and were considered to be excessive for a new generation helicopter.
| Author | : Randall W. Cason |
| Publisher | : |
| Total Pages | : 178 |
| Release | : 1988 |
| Genre | : Helicopters |
| ISBN | : |
Download Airworthiness and Flight Characteristics Test of the UH-60A Black Hawk Helicopter Equipped with the XM-139 Multiple Mine Dispensing System (VOLCANO) Book in PDF, ePub and Kindle
| Author | : Randall W. Cason |
| Publisher | : |
| Total Pages | : 127 |
| Release | : 1987 |
| Genre | : |
| ISBN | : |
Download Airworthiness and Flight Characteristics Test of a Ski Assembly for the UH-60A Black Hawk Helicopter Book in PDF, ePub and Kindle
An Airworthiness and Flight Characteristics test of the UH-60A helicopter (S/N 84-23953) configured with a ski assembly was conducted by the U.S. Army Aviation Engineering Flight Activity. The test was conducted at the Sikorsky Flight Test Facility at West Palm Beach, Florida (elevation 28 feet). A total of 25.5 productive flight hours were flown during the period 6 to 30 April 1987. Tests were conducted to determine the handling qualities and performance decrement of the ski assembly on the UH-60A helicopter at average mission gross weights of approximately 16,000 and 22,000 pounds. The handling qualities of the UH-60A with the ski assembly installed were essentially unchanged from those previously reported for the normal utility UH-60A. Two previously reported shortcomings are still evident: neutral static longitudinal stability during intermediate rated power climbs, and self-excited aircraft pitch oscillation with the collective control raised sufficiently for the aircraft to be 'light' on its wheels. The equivalent flat plate area of the ski assembly was determined to be 3 square feet. Several miscellaneous observations were made regarding the effects of the ski installation.
| Author | : M. L. Hanks |
| Publisher | : |
| Total Pages | : 158 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
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 | : Arthur R. Marshall |
| Publisher | : |
| Total Pages | : 88 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
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.
| Author | : J. I. Nagata |
| Publisher | : |
| Total Pages | : 45 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
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.
| Author | : |
| Publisher | : Jeffrey Frank Jones |
| Total Pages | : 962 |
| Release | : |
| Genre | : |
| ISBN | : |
Download Manuals Combined: UH-60 BLACK HAWK Pilot Flight Training, Engine, Electrical, Fuel System, Instrument & Crew Functions Visual Training Materials Book in PDF, ePub and Kindle
Over 900 pages ... Just a sample of the contents: LANDING GEAR TERMINAL LEARNING OBJECTIVE ACTION: Determine the major components and operational characteristics of the UH-60 landing gear system. CONDITIONS: Given multiple choices, visual representations of the UH-60 landing gear system components, and applicable references. STANDARDS : Select from multiple choices, the major components and operating characteristics of the UH-60 landing gear system. SAFETY REQUIREMENTS- Use care when operating training aids and/or devices. RISK ASSESSMENT- Low. ENVIRONMENTAL CONSIDERATIONS- None. EVALUATION: This block of instruction will be tested on the UH-60 aviation subjects written examination I (011-1374). A minimum score of 70% is required for passing. LEARNING STEP / ACTIVITY 1 Identify the primary components and operational characteristics of the UH-60 main landing gear system. Crash Worthiness UH-60 Main Landing Gear System Description: conventional, non-retractable, reverse tricycle arrangement. Components: Drag beam. Axle assembly. Main shock strut. Main wheel assembly. Wheel brake. Drag Beam Drag Beam Switches Drag Beam Strut at Rest Strut Under High Impact Load Strut Airborne Kneeling Valves Main Wheel Tire Details Master Cylinders Slave Cylinders/Parking Brake Valve Parking Brake Schematic Brake Wear Check Check On Learning Question: The lower stage of the main landing gear struts is designed to absorb landing loads up to ____ feet per second. Answer: 10 LEARNING STEP / ACTIVITY 2 Identify the primary components and operational characteristics of the UH-60 tail landing gear system. UH-60 Tail Landing Gear System Tail landing gear. Operation. Tail wheel assembly. Swivels 360 degrees. Upper end of strut. Yoke of tail gear. Fork assembly. Split aluminum rim. Tail wheel lock system. Tail Landing Gear Assembly Tail Strut Tail Yoke and Fork Tailwheel Lock System Tail Wheel Lock Check On Learning Question: Power to operate the tail wheel lock system is provided through the ____ bus. Answer: DC essential. SUMMARY Identified the primary components and operational characteristics of the UH-60 main landing gear system. Identified the primary components and operational characteristics of the UH-60 tail landing gear system. BREAK TIME! POWERTRAIN AND ROTOR SYSTEM TERMINAL LEARNING OBJECTIVE ACTION: Determine the major components and operational characteristics of the UH-60 powertrain system. CONDITIONS: Given multiple choices, visual representations of the UH-60 powertrain system components, and applicable references. STANDARDS : Select from multiple choices, the major components and operating characteristics of the UH-60 powertrain system. SAFETY REQUIREMENTS- Use care when operating training aids and/or devices. RISK ASSESSMENT- Low. ENVIRONMENTAL CONSIDERATIONS- None. EVALUATION: This block of instruction will be tested on the UH-60 aviation subjects written examination I (011-1374). A minimum score of 70% is required for passing. ENABLING LEARNING OBJECTIVE A ACTION: Identify the operational characteristics and modules of the UH-60 main transmission system. CONDITIONS: Given multiple choices, visual representations of the UH-60 main transmission system, and applicable references. STANDARDS: Select from multiple choices, the characteristics of the UH-60 main transmission system. Main Transmission Location Main Transmission Components Input and Accessory Modules Freewheeling Unit Accessory Module Main Module Details Check On Learning Question: The UH-60 main transmission system consists of how many modules? Answer: 5 (five). ENABLING LEARNING OBJECTIVE B ACTION: Identify the characteristics of the UH-60 main transmission lubrication system components. CONDITIONS: Given multiple choices, visual representations of the UH-60 transmission lubrication system, and
| Author | : Allen H. McCoy |
| Publisher | : |
| Total Pages | : 96 |
| Release | : 1997-12 |
| Genre | : Science |
| ISBN | : |
Download Flight Testing and Real-Time System Identification Analysis of a UH-60A Black Hawk Helicopter with an Instrumented External Sling Load Book in PDF, ePub and Kindle
Historically, helicopter and load combinations have been qualified through flight testing, requiring considerable time and cost. With advancements in simulation and flight test techniques, there is potential to substantially reduce costs and increase the safety of helicopter sling load certification. Validated simulation tools make possible accurate prediction of operational flight characteristics before initial flight tests. Real time analysis of test data improves the safety and efficiency of the testing programs. To advance these concepts, the US Army and NASA, in cooperation with the Israeli Air Force and Technion, under a Memorandum of Agreement, seek to develop and validate a numerical model of the UH-60 with sling load and demonstrate a method of near real time flight test analysis. This thesis presents results from flight tests of a US Army Black Hawk helicopter with various external loads. Tests were conducted as the US first phase of this MOA task. The primary load was a container express box (CONEX), which contained a compact instrumentation package. The flights covered the airspeed range from hover to 70 knots. Primary maneuvers were pitch and roll frequency sweeps, steps, and doublets. Results of the test determined the effect of the suspended load on both the aircraft's handling qualities and it's control system's stability margins. Included were calculations of the stability characteristics of the load's pendular motion. Utilizing CIFER software, a method for near-real time system identification was also demonstrated during the flight test program.
| Author | : Robert M. Buckanin |
| Publisher | : |
| Total Pages | : 115 |
| Release | : 1985 |
| Genre | : |
| ISBN | : |
Download Airworthiness and Flight Characteristics Test of a Sixth Year Production UH-60A. Book in PDF, ePub and Kindle
Testing was conducted to obtain performance data for inclusion in the sixth year production UH-60A helicopter operator's manual. A total of 58 productive flight hours were flown at five different test sites between 3 and 20 October 1983 and 29 February and 18 September 1984. The out-of-ground effect hover gross weight capability was 16,526 pounds for 95 percent intermediate (30 minute limit) rated power available at 4700 feet pressure altitude and 35 C temperature. The increase in equivalent flat plate area of the sixth year production aircraft configuration over the first year configuration over the first year configuration was 5 square feet in level flight at a referred rotor speed (N sub R/sqare rot theta) of 258 revolutions per minute. Of this increase, 2.5 was attributed to the External Stores Support System fixed provision fairings, 1.5 sq ft to the external mounting brackets of the AN/ALQ-144(V) infrared countermeasures set and M130 chaff dispenser, and 1.0 sq ft to numerous other minor external changes. However, throughout the N sub R/square root theta range, the difference in power required between the first and sixth year production aircraft does not equate to a constant Fe. A limited investigated did not completely account for the power differences noted when flying at different dimensional conditions that produce the same nondimensional thrust coefficient.
| Author | : James D. Brown |
| Publisher | : |
| Total Pages | : 160 |
| Release | : 1988 |
| Genre | : |
| ISBN | : |
Download Airworthiness and Flight Characteristics Evaluation of an Improved Engine Air Filtration System on the UH-1H Helicopter Book in PDF, ePub and Kindle
The U.S. Army Aviation Engineering Flight Activity conducted an Airworthiness and Flight Characteristics evaluation of the UH-1H aircraft with an Improved Engine Air Filtration System (IEAFS) installed and with the standard filter installed between 16 September 1987 and 29 February 1988. Aircraft performance and handling qualities, engine-air induction system compatibility, and engine performance with the IEAFS installed were evaluated. This evaluation was conducted at Edwards AFB, California. Twenty-five flights were conducted for a total of 20.1 productive flight hours. The aircraft performance and handling qualities, engine vibrations, and inlet temperature characteristics with the IEAFS installed are not significantly different from those of the standard UH-1H. The inlet pressure distortion and engine installation losses with the IEAFS installed are less than those of the standard UH-1H. One deficiency, the poor reliability of the IEAFS latch rivets, was identified. One shortcoming, the poor reliability of the latch lever locking device, was identified. Both the deficiency and the shortcoming should be corrected before production. Engine installation losses, Engine vibrations, Engine air filtration system, Inlet pressure distortion, Inlet temperature characteristics, Performance, Handling qualities, Standard filter. (mjm).
