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.

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.

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).

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

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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).

Report of the Engineering Flight Test -- Stability and Control 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 -- Stability and Control 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: 323

ISBN-13:

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Stability and control flight tests were conducted on the OH-4A helicopter to determine the stability and control characteristics throughout the flight envelope for the unarmed (clean) and armed configurations. Ninety-three test flights were conducted for 75:30 hours productive test time. All test data were hand recorded from sensitive instruments or recorded on an oscillograph. The quantitative test results and qualitative pilot's comments indicate that the OH-4A complied with most of the stability and control requirements of MIL-H-8501A.

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

Author:

Publisher:

Published: 1964

Total Pages: 275

ISBN-13:

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Stability and control tests were conducted on the OH-5A helicopter to determine stability and control characteristics throughout the flight envelope. In addition, XM-7 and XM-8 firing tests were conducted to define the aircraft's suitability for use as a weapons platform.

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.

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.

Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-20 Armament Subsystem (automatic 20mm Cannon).
Engineering Flight Test of the Ah-1g Helicopter Equipped with the Xm-20 Armament Subsystem (automatic 20mm Cannon).

Author: Stephen G. Dorris

Publisher:

Published: 1968

Total Pages: 30

ISBN-13:

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The engineering flight test of the AH-1G helicopter equipped with the XM-20 armament subsystem (automatic 20MM cannon) was conducted at Fort Hood, Texas from 31 January 1968 through 2 February 1968 by the US Army Aviation Test Activity, Edwards Air Force Base, California. Firing and nonfiring flight tests were conducted to determine the effects on the stability and control characteristics of the AH-1G helicopter caused by installation of the XM-20 armament subsystem. These tests were primarily qualitative in nature with limited qualitative data. The only stability and control characteristic which was affected either in the firing or nonfiring mode was the static longitudinal cyclic position gradients which were low at high speeds. The deficiencies detected during this test were the interference of the XM-20 gearbox with the XM-159 rocket pod and unreliability of the standard airspeed system due to the location of the static port in proximity to the XM-20 blast pressures. One firing rate of 600-800 spm is considered optimum. The XM-20 appears to offer greater stand-off capability, greater accuracy and more killing power than 2.75 inch rockets. It appears to be a reliable subsystem. The XM-20 configuration should be finalized, installed on a production AH-1G helicopter and certified for airworthiness throughout the AH-1G flight envelope as soon as possible to allow early introduction to Republic of Vietnam. (Author).

Handling Qualities Evaluation of the OH-58A Helicopter Incorporating the Model 570B Three-axis Stability and Control Augumentation System
Handling Qualities Evaluation of the OH-58A Helicopter Incorporating the Model 570B Three-axis Stability and Control Augumentation System

Author: Raymond B. Smith

Publisher:

Published: 1973

Total Pages: 90

ISBN-13:

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A limited handling qualities evaluation of the OH-58A helicopter with a Bell Helicopter Model 570B three-axis stability and control augmentation system installed was conducted to determine its capability to perform instrument flight. Testing was performed by the US Army Aviation Systems Test Activity at Edwards Air Force Base, California. The testing consisted of 25 productive flight hours and was conducted from September through November 1972. The evaluation revealed significant improvements in the aircraft handling qualities with the addition of the augmentation system. The most significant enhancing characteristics provided by the equipment were: (1) increased damping of the lateral-directional oscillation (Dutch roll), (2) improvement of aircraft spiral stability from neutral to convergent, and (3) reduction in pilot effort required to maintain trim flight conditions. This evaluation was of limited scope, and primarily addressed handling qualities. It did not provide a basis to qualify the aircraft for instrument flight.