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.
Download or read book Airworthiness and Flight Characteristics Test of an OH 58C Configured to a Light Combat Helicopter LCH written by and published by . This book was released on 1981 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a limited airworthiness and flight characteristics test of the OH-58C Light Combat Helicopter (LCH) from 22 July through 9 September 1981. The OH-58C LCH configuration increases the gross weight of the helicopter to 3425 pounds and includes one 7-tube 2.75-inch rocket pod and one 7.62mm minigun mounted externally. Performance and handling qualities were evaluated. A total of 20 flights were conducted for a total of 26.0 flight hours. As a result of the increased maximum gross weight of the OH-58C LCH, the hover ceiling was reduced. Level flight performance was degraded by the LCH configuration. No significant handling qualities differences were noted when comparing test results for the OH-58C LCH to the test results of the standard OH-58C.
Download or read book Airworthiness and Flight Characteristics of the JOH 58C OH 58X Surrogate Helicopter written by James L. Webre and published by . This book was released on 1986 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt: The US Army Aviation Engineering Flight Activity conducted a limited airworthiness and flight characteristics test of the JOH-58C Light Combat Helicopter (LCH) from 27 June through 23 October 1985. The JOH-58C LCH configuration includes a stability augmentation system manufactured by the SFENA Corporation and a larger-diameter tail rotor. Handling qualities were evaluated at test sites from near sea level (488 feet) to 9980 feet. A total of 49 flights were conducted for a total of 34.6 productive flight test hours. Primary emphasis during the evaluation was placed on evaluating the handling qualities of the JOH-58C in comparison to the standard OH-58C. The overall handling qualities of the JOH-58C were significantly improved as compared to the standard OH-58C. The JOH-58C exhibited less than 10% longitudinal control margin in rearward flight at speeds of approximately 17 knots and above at azimuths between 180 and 210 degrees. This characteristic is a deficiency. The pitch, roll and yaw excursions during low speed flight of the JOH-58C are significantly reduced as compared to the standard OH-58C. These handling qualities characteristics, which were a deficiency in the OH-58C, have been improved shortcomings or were eliminated under the conditions tested in the JOH-58C. Two additional shortcomings were identified in maneuvering flight.
Download or read book Preliminary Airworthiness Evaluation OH 58C Helicopter Configured with a Mast Mounted Sight written by and published by . This book was released on 1980 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a preliminary airworthiness evaluation of the OH-58C helicopter with a mast mounted sight and Bell Helicopter, Textron Model 570B three-axis stability and control augmentation system. The evaluation was completed in two phases at the Bell Helicopter Engineering Flight Research Center, Arlington, Texas (elevation 630 ft). Phase 1 consisted of an evaluation of a dummy mast mounted sight installed on an instrumented helicopter. This phase was conducted between 15 and 30 October 1980 and 12 flights were flown for a total of 9.7 productive hours. Phase 2 consisted of a qualitative assessment of the handling qualities of the OH-58C configured with the operational Rockwell International sight. This phase was completed on 30 November 1980 in two flights for 1.5 productive test flight hours. The overall evaluation indicated that the OH-58C handling qualities with installed mast mounted sight and three-axis SCAS were satisfactory within the flight envelope tested. No problems were noted that will prevent future operational testing of the system. The addition of a three-axis SCAS significantly improved the OH-58C handling qualities, particularly in low speed flight, and is an enhancing characteristic.
Download or read book Preliminary Airworthiness Evaluation OH 58C Helicopter written by and published by . This book was released on 1978 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a Preliminary Airworthiness Evaluation of the OH-58C helicopter from 21 February through 4 March 1978 at Arlington, Texas. Eighteen flights consisting of 14.7 hours of productive flight test time were flown while conducting a limited handling qualities evaluation of the aircraft. Testing was conducted primary at maximum gross weight (3200 pounds) and aft center of gravity (fuselage station 112) conditions. The possibility of inadvertent activation of the night vision goggle switch located on the pilot cyclic control grip was identified as a deficiency. Activation of this switch during day flight rendered the warning and caution lights unreadable. The most significant difference in flying qualities between the OH-58C and the OH-58A was pitch-up tendency at cruise airspeed and aft center of gravity, which is a shortcoming. Insufficient left directional control in right sideward flight, excessive yaw oscillations in left sideward flight between 15 and 39 knots true airspeed, and excessive pitch and yaw oscillations in rearward flight are also shortcomings. Eight additional shortcomings were noted. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1980 with total page 1280 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1983 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Evaluation UH 60A Black Hawk Helicopter written by John I. Nagata and published by . This book was released on 1981 with total page 267 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1980 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP written by and published by . This book was released on 1981 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Airworthiness Evaluation of the OH 58C with 3 Axis Stability Control Augmentation System and Improved Tail Rotor System written by M. L. Hanks and published by . This book was released on 1983 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt: This preliminary airworthiness evaluation was conducted on an OH-58C helicopter configured with a 3-axis digital stability control augmentation system (SCAS) and an improved tail rotor. Additional testing on the standard OH-58C equipped with the 3-axis SCAS was required in response to questions which surfaced during working sessions of the Joint Special Study Group investigating 0H-58 loss of tail rotor effectiveness. Testing was accomplished at Arlington, TX (elevation 630 feet), Leadville, CO (elev. 9927 feet) and Alamosa, CO (elev. 7535 feet). Test time totaled 44.2 productive flight test hours. With the improved tail rotor, adequate directional control margins were available for flight at all azimuths out to the wind limits (35 KTAS sideward and 30 KTAS rearward) of the aircraft at density altitudes up through 11,000 feet for a gross weight of 3,040 lb. The overall handling qualities of the OH-58C helicopter equipped with a 3-axis digital SCAS in either tail rotor configuration were significantly improved over the unaugmented aircraft configuration except as stated in the report. TWo handling quality deficiencies were noted.
Download or read book Airworthiness and Flight Characteristics Test Production OH 58A Helicopter Unarmed and Armed with XM27E1 Armament Subsystem Stability and Control written by William A Graham (Jr) and published by . This book was released on 1970 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: Stability and control tests were conducted on a production model OH- 58A helicopter to evaluate its flying qualities in the unarmed configuration and in an armed configuration with the XM27E1 weapon system. Limited testing was also performed to evaluate the helicopter slope landing capabilities and flying qualities with skis installed. Human factors and maintainability characteristics were noted throughout the evaluation. The testing consisted of 89 flights which totaled 85.3 hours of productive flight testing. Maintainability of the helicopter was excellent throughout the test program.
Download or read book Aeronautical Engineering written by and published by . This book was released on 1980 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Download or read book Maintenance Test Flight Manual written by and published by . This book was released on 1982 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Evaluation AH 1Q Helicopter written by Leslie J. Hepler and published by . This book was released on 1973 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Test CH 47C Helicopter Chinook written by Robert F. Forsyth and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Airworthiness and Flight Characteristics Evaluation Iranian Model 214A Helicopter written by William R. Horton and published by . This book was released on 1975 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
