Download or read book Instrument Flight Evaluation AH 1G Helicopter written by Gary L. Skinner and published by . This book was released on 1975 with total page 123 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited evaluation of handling qualities and operational performance was conducted on the AH-1G helicopter to determine its suitability for operation under instrument flight conditions with the stability and control augmentation system ON and OFF are discussed. Tests were conducted intermittently from February 1973 to December 1974. Ten shortcomings were identified, and it is recommended that two of these should be corrected prior to release for flight in instrument conditions.
Download or read book Flight Test Guide written by United States. Flight Standards Service and published by . This book was released on 1977 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance and Handling Qualities Evaluation AH 1G Helicopter with Low Reflective Infrared optical Paint written by Albert L. Winn and published by . This book was released on 1975 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance and handling qualities of an AH-1G helicopter were evaluated in the basic paint configuration, with the fuselage and main and tail rotors painted with a low reflective infrared (IR)/optical paint (FSN 8010-083-6588), and in a modified IR/optical paint configuration in which the tail rotor blades and the main rotor leading edge were stripped of the IR/optical paint. Flight tests were conducted by the United States Army Aviation Engineering Flight Activity at Edwards Air Force Base, California, between 27 November 1974 and 10 April 1975. Twenty-five flights were flown for a total of 24.7 productive flight hours. Performance testing was limited to hover, level flight, and autorotational descent. Handling qualities were qualitatively evaluated throughout the conduct of the test program. Additionally, maneuvering stability was quantitatively evaluated in the IR/optical paint configuration and compared with results from previous reports.
Download or read book Engineering Flight Test AH 1G Helicopter Heavyweight Autorotational Evaluation written by Joseph C. Watts and published by . This book was released on 1974 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Engineering flight tests were conducted by the United States Army Aviation Systems Test Activity to determine if any adverse autorotational entry or landing characteristics would preclude increasing the maximum operational gross weight of the AH-1G helicopter above the current 9500 pounds. A production AH-1G helicopter with tractor tail rotor was flown 14.4 hours at Edwards Air Force Base, California between 26 September and 12 October 1973 in the Hog configuration. Autorotational entries were performed successfully at gross weights from 9000 to 10,000 pounds from climbs, level flight, and dives. (Modified author abstract).
Download or read book Evaluations of Helicopter Instrument flight Handling Qualities written by S. R. M. Sinclair and published by . This book was released on 1982 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AH 1G Lateral Flight Performance Test written by Leslie J. Hepler and published by . This book was released on 1972 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lateral flight performance of the tractor-tail-rotor-configured AH-1G helicopter was evaluated at gross weights of 8500 and 9500 pounds. The AH-1G is capable of 0.53g and 0.38g accelerations in right and left lateral flight, respectively, at 8500 pounds. At a 9500-pound gross weight, acceleration was 0.23g to the right and 0.20g to the left. Aircraft handling qualitites and time required to attain maximum lateral velocity are dependent upon rate and type of control application. A step-type lateral control input permitted rapid attainment of accelerating attitude but produced yaw oscillations which resulted in loss of directional control and caused high pilot workload in stabilizing power and aircraft attitude. Ramp inputs delayed establishment of the accelerating attitude. A modified pulse input induced negligible roll and yaw oscillation and produced rapid establishment of the desired roll attitude. Direction-of-flight reversals induced large power transients that frequently exceeded the transmission torque limits. Precise heading and pitch attitude could not be maintained during the reversals. Airspeed in lateral flight could not be determined without special airspeed measuring devices. The sideward airspeed limit was exceeded frequently in left lateral flight with no warning or cue to the pilot that the limit had been reached.
Download or read book Artificial Icing Tests AH 1G Helicopter written by Carl F. Mittag and published by . This book was released on 1974 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Engineering Flight Activity conducted a limited in-flight artificial icing evaluation of the AH-1G helicopter from 22 October through 6 November 1973 at Fort Wainwright, Alaska, and from 22 March through 2 April 1974 in the vicinity of Moses Lake, Washington. During the test program 8.5 hours of productive flight time were flown, of which 4.0 hours were in the artificial icing environment. Three deficiencies were noted which adversely affect the safe operation of the AH-1G helicopter in an icing environment.
Download or read book Engineering Flight Test AH 1G Helicopter with Model 212 Tail Rotor Part II Performance and Handling Qualities written by John I. Nagata and published by . This book was released on 1973 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Systems Test Activity conducted a limited performance and handling qualities evaluation of the AH-1G helicopter with a Bell Helicopter Company commercial Model 212 tail rotor installed. This installation included changes to the pitch links and pitch control tube to accommodate the Model 212 tail rotor; however, the remaining components of the tail rotor drive system were standard AH-1G items. The evaluation was performed during the period 29 May to 7 August 1973 at Edwards Air Force Base, Bakersfield, and Bishop, California. (Modified author abstract).
Download or read book Airworthiness and Flight Characteristics Test AH 1G Helicopter with Stabilized Night Sight SNS Phase II written by Gary L. Bender and published by . This book was released on 1970 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Phase II tests were conducted to evaluate the flight envelope of the AH-1G with the SNS installed for significant changes in the structural loads, handling qualities and performance due to this modification. The effects of weapons firing on the SNS system were also evaluated. The structural loads, handling qualities and performance of the AH-1G were not significantly changed by the SNS installation. The published AH-1G flight envelope is satisfactory for the SNS modified aircraft with one exception: due to the aircraft's reactions following sudden engine failure, the engine torque should be limited to less than 35 pounds per square inch, indicated, for all dives to airspeeds greater than 150 KCAS. Four deficiencies require correction before further testing in instrument flight conditions or in a combat environment.
Download or read book Instrument flight rules Evaluation AH1 G Helicopter with Tractor Tail Rotor written by John R. Burden and published by . This book was released on 1972 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering Flight Test of the Ah 1g Helicopter hueycobra Phase B written by John R. Melton and published by . This book was released on 1968 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part 1 of the AH-1G helicopter Phase B test was conducted at Ft Hood, Texas by the US Army Aviation Test Activity, Edwards AFB, California. The helicopter flying qualities were evaluated throughout the aircraft speed range for the Scout and Hog configurations at a mid-center-of-gravity location. Flying qualities were also evaluated during weapons firing and external stores jettison. The primary deficiencies detected during this test were stability and Control augmentation system (SCAS)-pylon coupling, inadequate in-ground-effect (IGE) directional control power, undue pilot attention required to avoid exceeding the torque limits of the helicopter transmission in dives and left rolls with fixed collective, and an inadequate, illogical fire control system. Other shortcomings were detected, such as airspeed system errors, degradation of flying qualities with SCAS off, static lateral cyclic control force imbalance, and marginal cockpit ventilation. Helicopter reactions to weapons firing and external stores jettison were satisfactory, and the contractor approved flight envelope for firing and jettison was acceptable.
Download or read book Height Velocity Test AH 1G Helicopter at Heavy Gross Weight Part 1 Low Elevation written by and published by . This book was released on 1974 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: The United States Army Aviation Systems Test Activity conducted engineering flight tests to determine the operational height-velocity envelopes of the AH-1G helicopter at 9000 and 9500 pounds gross weight. This report constitutes the low elevation part of the evaluation conducted at Edwards Air Force Base, California, from 14 November 1973 through 5 February 1974. Operational height-velocity envelopes were defined from test data, are valid for 9000 and 9500 pounds at density altitudes up to 1000 feet, and represent combinations of airspeed and height above ground level where a straight-ahead landing may be accomplished following an engine failure. Autorotational landings at gross weights over 9250 pounds will probably result in rotor overspeed and the height above ground level at which the flare is executed becomes more critical as gross weight is increased to 9500 pounds. The operator's manual lacks clarity in describing pilot techniques to be used during the height-velocity maneuver and needs improvement in other areas. The height-velocity diagram developed during this evaluation, a discussion of the height-velocity diagram, a more thorough discussion of pilot techniques, the correct airspeed calibration chart, and the hog configuration descent performance chart should be incorporated in the operator's manual. A radio altimeter should be installed as standard equipment on the AH-1G helicopter.
Download or read book Engineering Flight Test AH 1G HueyCobra Helicopter Autorotational Entry Characteristics written by Brock M. Nicholson and published by . This book was released on 1971 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1990 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The 1980 Guide to the Evaluation of Educational Experiences in the Armed Services Army written by American Council on Education and published by . This book was released on 1980 with total page 852 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The 1984 Guide to the Evaluation of Educational Experiences in the Armed Services written by American Council on Education and published by . This book was released on 1984 with total page 852 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Engineering Flight Test of the Ah 1g Helicopter Equipped with the Xm 28 Chin Turret with One 7 62mm Automatic Gun m 134 and One 40mm Grenade Launcher xm 129 hybrid Phase B written by Peter V. Passinisi and published by . This book was released on 1968 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part 5 of the AH-1G helicopter Phase B test was conducted at Yuma Proving Ground, Yuma, Arizona, from 6 through 9 February 1968 by the US Army Aviation Test Activity, Edwards Air Force Base, California. The test consisted of firing the XM-28 chin turret, with one 7.62 millimeter automatic gun (M-134) and one 40 millimeter grenade launcher (XM-129) to determine the weapons system's effect on the stability and control characteristics of the helicopter. No safety of flight restrictions resulted from firing this system within the flight envelope. Correction of four deficiencies is mandatory to provide acceptable mission effectiveness and safety. These deficiencies are the inadequate forward visibility from the pilot's cockpit due to the N-9A gunsight installation, the lack of a fire warning system, the lack of a standby generator for IFR flight, and link jam malfunctions of the minigun during symmetrical pull-out maneuvers. Fifteen shortcomings, for which correction is desirable, limit mission effectiveness. The reliability of the weapons system was questionable and service type testing should be conducted prior to system acceptance. Correction of the deficiencies is mandatory and should be tested prior to deployment. Shortcomings, for which correction is desirable, should be corrected on a high priority basis. (Author).
