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.

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 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).

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.

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).

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 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:

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.

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 Apache Helicopter Tests Results for the 30 millimeter Weapon System Inconclusive written by United States. General Accounting Office and published by . This book was released on 1993 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

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 and published by . This book was released on 1988 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

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 Army Preliminary Evaluation YOH 58A Helicopter with a Flat Plate Canopy written by James R. Arnold and published by . This book was released on 1975 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited evaluation of the performance and handling qualities of the OH-58A helicopter was conducted to determine the effects of a four-plane flat-plate canopy installation. Testing was conducted at the Bell Helicopter Company flight test facility at Arlington, Texas, from 25 October through 4 November 1975. Personnel from the United States Army Aviation Engineering Flight Activity conducted 11 test flights for a total of 6.5 productive test flight hours. The evaluation revealed a loss in airspeed of 2 and 6 knots at the airspeed for maximum continuous power and a loss in range of 8 and 23 nautical miles at the cruise airspeed (forward and aft center-of-gravity configurations, respectively). The noticeable changes in the handling qualities were a slight increase in the nose-down pitching rate following a sudden loss of power (more pronounced for the forward center-of-gravity configuration) and a slight increase in the dihedral effect of the helicopter. The flat-plate canopy installation resulted in a slight reduction in the field of view, but visibility was improved due to the optical clarity of the flat-plate. The installation of glare shields between the chin bubble and canopy significantly reduced the canopy reflections during both day and night tests. One shortcoming was noted during this evaluation but cannot be attributed to the flat-plate canopy installation. (Author).

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).