Airworthiness and Flight Characteristics Test Production OH-58A Helicopter Unarmed and Armed with XM27E1 Weapon System, Performance
Airworthiness and Flight Characteristics Test Production OH-58A Helicopter Unarmed and Armed with XM27E1 Weapon System, Performance

Author: George M. Yamakawa

Publisher:

Published: 1970

Total Pages: 132

ISBN-13:

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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.

Airworthiness and Flight Characteristics Test, Production OH-58A Helicopter Unarmed and Armed with XM27E1 Armament Subsystem, Stability and Control
Airworthiness and Flight Characteristics Test, Production OH-58A Helicopter Unarmed and Armed with XM27E1 Armament Subsystem, Stability and Control

Author: William A Graham (Jr)

Publisher:

Published: 1970

Total Pages: 162

ISBN-13:

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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.

Engineering Flight Test (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D
Engineering Flight Test (product Improvement Test) of Production Oh-6a Helicopter Unarmed and Armed with the Xm-27e1 Weapon System Phase D

Author: John I. Nagata

Publisher:

Published: 1968

Total Pages: 80

ISBN-13:

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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).

Army Preliminary Evaluation, Prototype OH-58A Helicopter with XM27E1 Weapon Subsystem
Army Preliminary Evaluation, Prototype OH-58A Helicopter with XM27E1 Weapon Subsystem

Author: John Nagata

Publisher:

Published: 1970

Total Pages: 59

ISBN-13:

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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).

Climatic Laboratory Test. OH-58A Helicopter Equipped with XM27E1 Machine Gun Armament System
Climatic Laboratory Test. OH-58A Helicopter Equipped with XM27E1 Machine Gun Armament System

Author: Daniel G. Tyson

Publisher:

Published: 1970

Total Pages: 138

ISBN-13:

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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.

Airworthiness and Flight Characteristics Evaluation. OH-58C Interim Scout Helicopter
Airworthiness and Flight Characteristics Evaluation. OH-58C Interim Scout Helicopter

Author:

Publisher:

Published: 1979

Total Pages: 205

ISBN-13:

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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.

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
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

Author: ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CA.

Publisher:

Published: 1964

Total Pages: 110

ISBN-13:

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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.

Report of the Engineering Flight Test -- Performance Phase -- OH-5A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem
Report of the Engineering Flight Test -- Performance Phase -- OH-5A Helicopter, Unarmed (Clean) and Armed with the XM-7 Or XM-8 Weapon Subsystem

Author:

Publisher:

Published: 1964

Total Pages: 110

ISBN-13:

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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.

Airworthiness and Flight Characteristics Test of an OH-58C Configured to a Light Combat Helicopter (LCH).
Airworthiness and Flight Characteristics Test of an OH-58C Configured to a Light Combat Helicopter (LCH).

Author:

Publisher:

Published: 1981

Total Pages: 99

ISBN-13:

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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.