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Airworthiness And Flight Characteristics Test Production Oh 58a Helicopter Unarmed And Armed With Xm27e1 Weapon System Performance
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Book Synopsis Airworthiness and Flight Characteristics Test Production OH-58A Helicopter Unarmed and Armed with XM27E1 Weapon System, Performance by : George M. Yamakawa
Download or read book Airworthiness and Flight Characteristics Test Production OH-58A Helicopter Unarmed and Armed with XM27E1 Weapon System, Performance written by George M. Yamakawa and published by . This book was released on 1970 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: Performance tests were conducted on a production OH-58A helicopter to determine compliance with performance guarantees outlined in the detail specification and approved revisions, and also to provide information for the operator's manual. The testing consisted of 99 flights totaling 62.5 productive hours. The OH-58A met or exceeded all of the contractual performance guarantees. The engine inlet loses with the particle separator installed exceeded the limits of the detail specification. A single flight at cold temperatures indicated that level flight performance is significantly affected by compressibility. Although all contractual hover performance guarantees were met, the helicopter could not hover out of ground effect on a 95 F day at gross weights greater than 2930 pounds with the particle separator installed. Under moderate temperature conditions, the performance capabilities of the OH-58A are satisfactory for mission accomplishment. It is recommended that consideration be given to increasing the utility of the OH-58A by installing a more powerful engine.
Book Synopsis Airworthiness and Flight Characteristics Test, Production OH-58A Helicopter Unarmed and Armed with XM27E1 Armament Subsystem, Stability and Control by : William A Graham (Jr)
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.
Book Synopsis Engineering Flight Test (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D by : John I. Nagata
Download or read book Engineering Flight Test (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D written by John I. Nagata and published by . This book was released on 1968 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: An engineering flight test of the OH-6A helicopter equipped with the XM-27E1 armament subsystem was conducted at Edwards Air Force Base, California, by the US Army Aviation Test Activity. The objective of the test was to determine what effects the armament subsystem had on the performance and stability and control characteristics as compared with an aircraft without the armament subsystem. The testing consisted of 10.25 productive test hours and was conducted from 2 October 1967 through 24 October 1967. Performance degradation resulted from the drag imposed by the armament subsystem. The specific range at 2400 pounds gross weight decreased by 8 percent. The stability and control characteristics were essentially unchanged by the addition of the armament subsystem. During firing tests, there were no adverse control problems. However, during flight at 12 degrees left sideslip at 105 knots indicated airspeed (KIAS), the upper right windshield imploded. The sideslip angle should be limited to 8 degrees or less at 100 KIAS until the cause of the implosion can be determined. Noise level and vibration tests should be conducted during firing with the 'doors off' configuration. The performance data should be incorporated into the operator's manual. (Author).
Book Synopsis Army Preliminary Evaluation, Prototype OH-58A Helicopter with XM27E1 Weapon Subsystem by : John Nagata
Download or read book Army Preliminary Evaluation, Prototype OH-58A Helicopter with XM27E1 Weapon Subsystem written by John Nagata and published by . This book was released on 1970 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Army Preliminary Evaluation of the OH-58A prototype helicopter was conducted in the vicinity of Arlington, Texas, during the period 26 June to 9 July 1969. Thirteen test flights were conducted for a total of 14.5 hours of which 9.1 hours were productive. The evaluation consisted of limited quantitative and qualitative stability and control tests in the armed scout configuration only. The handling qualities of the OH-58A are satisfactory for the accomplishment of the armed scout mission. (Author).
Book Synopsis Optimal Landing of a Helicopter in Autorotation by : Allan Yeow-Nam Lee
Download or read book Optimal Landing of a Helicopter in Autorotation written by Allan Yeow-Nam Lee and published by . This book was released on 1985 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Climatic Laboratory Test. OH-58A Helicopter Equipped with XM27E1 Machine Gun Armament System by : Daniel G. Tyson
Download or read book Climatic Laboratory Test. OH-58A Helicopter Equipped with XM27E1 Machine Gun Armament System written by Daniel G. Tyson and published by . This book was released on 1970 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt: An environmental test was conducted in the Climatic Laboratory, Eglin Air Force Base (AFB), Florida, to determine the adequacy of the OH-58A helicopter for its intended use in extreme temperature environments. The pilot's body temperatures was recorded during the test. The testing consisted of 11 data runs for a total of 13.1 hours. The aircraft is generally acceptable for operation between 0 and 105 F. Operation of the aircraft above 105 F is limited by restriction of power available because of turbine outlet temperature limitations and by reduction of the pilot's ability to perform his required tasks because of fatigue. Operation of the aircraft below 0 F is limited by four deficiencies.
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 Report of the Engineering Flight Test -- Performance Phase -- of the OH-4A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem by : ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA.
Download or read book Report of the Engineering Flight Test -- Performance Phase -- of the OH-4A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem written by ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA. and published by . This book was released on 1964 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Performance flight tests were conducted on the OH-4A to determine the compliance with the Light Observation Helicopter (LOH) Military Characteristics and to Check the contractual guarantees outlined in the OH-4A Model Specification.
Book Synopsis Report of the Engineering Flight Test -- Performance Phase -- OH-5A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem by :
Download or read book Report of the Engineering Flight Test -- Performance Phase -- OH-5A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem written by and published by . This book was released on 1964 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Performance flight tests were conducted on the OH-5A helicopter to determine the compliance with the Light Observation Helicopter (LOH) Military Characteristics, to verify the contractual guarantees outlined in the OH-5A helicopter Model Specification and obtain additional data useful to the Selection Board.
Book Synopsis Airworthiness and Flight Characteristics Test of an OH-58C Configured to a Light Combat Helicopter (LCH). by :
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.
Book Synopsis Airworthiness and Flight Characteristics Test of the UH-60A Black Hawk Helicopter Equipped with the XM-139 Multiple Mine Dispensing System (VOLCANO) by : Randall W. Cason
Download or read book Airworthiness and Flight Characteristics Test of the UH-60A Black Hawk Helicopter Equipped with the XM-139 Multiple Mine Dispensing System (VOLCANO) written by Randall W. Cason and published by . This book was released on 1988 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Airworthiness and Flight Characteristics Test (A & FC) of the BHTI 214ST Helicopter by : Robert A. Williams
Download or read book Airworthiness and Flight Characteristics Test (A & FC) of the BHTI 214ST Helicopter written by Robert A. Williams and published by . This book was released on 1985 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Airworthiness and Flight Characteristics Test of the Bell 214ST helicopter (S/N N3186W) was conducted by the US Army Aviation Engineering Flight Activity (USAAEFA). The test was conducted at Edwards Air Force Base (elevation 2302 feet), Bakersfield (elevation 488 feet), Bishop (elevation 4120 feet) and Coyote Flats (elevation 9980 feet), California. A total of 62.6 hours (27.5 productive hours) were flown between 1 July and 27 August 1985. Hover, level flight and autorotational descent performance tests were conducted. Handling qualities tests included static and dynamic stability, maneuvering stability, power management, systems failures, mission maneuvers and flight in simulated Instrument Meteorological Conditions (IMC). The airspeed for best glide distance determined from the autorotational descent performance test results of this evaluation was significantly less than the best glide distance airspeed presented in the flight manual. The out-of-ground effect hover test results when compared to the flight manual indicated less hover capability at standard day conditions and altitude below 8060 feet but better hover capability at higher altitudes. The maximum difference between the flight manual and the test results of this evaluation was 250 pounds, below 8060 feet. Two major conclusions reached were: the 214ST is an excellent IMC aircraft with its IMC capabilities exceeding those of any US Army helicopters and its cockpit design significantly reduces pilot workload in most modes of flight.
Book Synopsis Airworthiness and Flight Characteristics Test of a Sixth Year Production UH-60A. by : Robert M. Buckanin
Download or read book Airworthiness and Flight Characteristics Test of a Sixth Year Production UH-60A. written by Robert M. Buckanin and published by . This book was released on 1985 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Army Preliminary Evaluation JOH-58A Helicopter with Low Reflective Paint and Infrared Countermeasure Exhaust System by : Charles L. Thomas
Download or read book Army Preliminary Evaluation JOH-58A Helicopter with Low Reflective Paint and Infrared Countermeasure Exhaust System written by Charles L. Thomas and published by . This book was released on 1975 with total page 107 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted an Army Preliminary Evaluation of a JOH-58A helicopter painted with a low reflective paint and equipped with a prototype infrared countermeasure exhaust system from 1 July through 14 October 1975. The testing was conducted at Edwards Air Force Base and at Point Mugu Naval Air Station, California. Results of these tests were compared with test results from earlier evaluations of the OH-58A performance and handling qualities characteristics and with preliminary base-line testing performed during this evaluation. One deficiency and two shortcomings were noted during this evaluation. Although not classified as a deficiency or shortcoming, the most significant finding in this evaluation was the serious degradation in hover and level flight performance when the rotor blades are painted with low reflective paint.
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 Airworthiness and Flight Characteristics of the JOH - 58C (OH-58X Surrogate) Helicopter by : James L. Webre
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.
Book Synopsis Airworthiness and Flight Characteristics (A & FC) Test of YAH-64 Advanced Attack Helicopter, Prototype Qualification Test-Government (PQT-G). Part 3 and Production Validation Test-Government (PVT-G) for Handbook Verification by : Bartholomew D Picasso (III.)
Download or read book Airworthiness and Flight Characteristics (A & FC) Test of YAH-64 Advanced Attack Helicopter, Prototype Qualification Test-Government (PQT-G). Part 3 and Production Validation Test-Government (PVT-G) for Handbook Verification written by Bartholomew D Picasso (III.) and published by . This book was released on 1982 with total page 273 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Airworthiness and Flight Characteristics Test of the YAH-64 helicopter was conducted. Seventy flights and 70.4 productive hours were flown. Performance testing assessed the probability of meeting the production contract requirements and consisted of an evaluation of hover, takeoff, level flight, forward flight climb and autorotational descent performance. Handling qualities testing determined compliance with selected research and development contract requirements and included standard stability and control tests, an evaluation of slope landing characteristics and instrument flight capability. Additional tests included evaluation of an uprated engine and an external noise survey. The YAH- 64 now meets the performance requirements of the system specification for the production program; the vertical climb and maximum level flight cruise speeds. Slope landing characteristics were satisfactory up to 9 degree lateral slopes and 10 degree longitudinal slopes.
