Download or read book Product Improvement Test of OH 6A Helicopter Tail Rotor Balancing Equipment written by James P. Maguire and published by . This book was released on 1968 with total page 4 pages. Available in PDF, EPUB and Kindle. Book excerpt: Maintenance problems associated with high-frequency vibrations in the OH-6A were encountered in the reliability test program and in tactical use by field units. These vibrations frequently were attributed to improper balance of the tail-rotor assembly. Since this assembly could not be balanced using equipment presently in the Army inventory, the LOH Project Manager requested that the airframe manufacturer develop suitable balancing equipment. The tail-rotor balancing equipment consists of an accelerometer with mounting bracket, a vibration analyzer, a protractor, and electrical cables, which are contained in a fiberglass carrying case. These items are used in conjunction with the blade-tracking strobe light assembly. Power required for equipment operation is 24 volt's direct current which is obtained from the auxiliary fuel tank connector in the aircraft.
Download or read book Product Improvement Test OH 6A Maintenance Platform written by ARMY AVIATION TEST BOARD FORT RUCKER ALA. and published by . This book was released on 1968 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this report was to determine the suitability of the maintenance platform for use on the OH-6A Helicopter.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Product Improvement Test Verification Test of the OH 58C Helicopter written by Stanley M. Niemiec and published by . This book was released on 1978 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Product Improvement Test of OH 58A Helicopter Cold Weather Test written by Jack D. Hill and published by . This book was released on 1970 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Product Improvement Test of Component TBO Extension UH 1 Helicopter written by ARMY AVIATION TEST BOARD FORT RUCKER ALA. and published by . This book was released on 1966 with total page 113 pages. Available in PDF, EPUB and Kindle. Book excerpt: The majority of UH-1() dynamic components are replaced for overhaul or retirement at 1100-hour intervals. The UH-1() flying-hour program in the Republic of Vietnam (RVN) is 70 hours per month. Extension of the time between overhaul (TBO)of major dynamic components of the UH-1B and UH-1D Helicopters is highly desirable to improve the world-wide UH-1() supply posture and the availability rate of aircraft affected, and to provide substantial monetary savings. TBO extensions should be based only on experience gained from overhauls and from operation of sufficient number of test components beyond the authorized TBO. A UH-1() TBO Committee Meeting was held at the airframe manufacturer's plant on 25 and 26 March 1965 to examine the dynamic components removed at the completion of the logistical evaluation of the UH-1B Helicopter (Serial number 63-8659) at high takeoff gross weight, USATECOM Project No. 4-3-0100-08. It was decided at the meeting that the only UH-1() components suitable for a TBO extension program were: (1) Main-rotor hub assembly, P/N 204-011-101-9. (2) Intermediate (42-degree) gearbox, P/N 204-040-003-23. (3) Tail-rotor (90-degree) gearbox, P/N 204-040-012-7.
Download or read book Product improvement Test of OH 58A Helicopter Cold Weather Test written by Richard J. Followill and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Major Item Special Study MISS OH 6A Tail Rotor Assembly written by ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO. and published by . This book was released on 1974 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report is designed to illustrate cost savings which would result from specific efforts in the areas of product improvement in quality and design. For the purpose of this study the cost savings produced in the area of product improvement are based on total elimination of a certain failure mode or modes. Appropriate modes are chosen because of their proportion of the total removals or their proportion in combination with other similar modes. These eliminated removals are then assumed to follow the distribution of the remaining removal modes. The actual cost savings are determined from the increase in the mean time to removal based on the new removal distributions.
Download or read book Process Improvements for the AH 64 Tail Rotor Vibration Analysis written by Mark C. Newkirk and published by . This book was released on 2007 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Final Report written by United States. Army Training and Doctrine Command and published by . This book was released on 1979 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Product Improvement Test Maintainability and Reliability Characteristics of the OH 58A Helicopter Between 1 200 and 2 400 Flight Hours written by ARMY AVIATION BOARD FORT RUCKER ALA. and published by . This book was released on 1972 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: Evaluation of data obtained during this test revealed no significant difference in the maintainability and reliability of the OH-58A Helicopter during the 1,200- through 2,400-flight-hour period as compared with the 0- through 1,200-flight hour period. Copies of the complete data printouts are attached for each of the test helicopters.
Download or read book Product Improvement Test of Engine Tail Pipe Indicator and Recorder Installed in UH 1B Helicopter written by ARMY AVIATION TEST BOARD FORT RUCKER ALA. and published by . This book was released on 1966 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Frequent, prolonged over-temperature events will severely limit the service life of any gas turbine engine and may result in catastrophic failure. Occasionally, these over-temperatures are not recorded accurately on the aircraft maintenance forms. An accurate, lightweight, automatic system for recording over-temperature events would provide valuable information for the proper maintenance of gas turbine engines, and for the timely removal of engines which have been subjected to temperatures beyond allowable limits. A test system was developed to provide a record of the frequency and duration of over-temperature events in addition to providing the pilot with an EGT indicator. The EGT recorder was designed to record the occurrence of temperatures above three significant, preselected values: 625 C. during the starting cycle only and 650 C. and 760 C. during flight operations. The United States Army Aviation Test Board (USAAVNTBD) was directed to test two EGT indicator-recorders installed in UH-1B/540 helicopters.
Download or read book Fatigue Test of OH 58A Main Rotor Blade P I P Task No 69 6 written by I. L. Reese and published by . This book was released on 1971 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: A fatigue test of a main helicopter rotor blade assembly was conducted as part of a product improvement program to increase the service life of the blade from the existing 1200 hours. Results are reported. (Author).
Download or read book The Correlation of Pedal Position to Tail Rotor Power Requirement on the OH 58A written by and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Every mechanical component has a finite failure life. Excessive usage of a component may cause damage. Therefore, life determination is essential to safe operation. Replacement of mechanical components prior to the end of useful life results in higher costs of maintenance. Monitoring rotating components is not always reliable or cost effective. This thesis attempts to solve this problem for a helicopter tail rotor. The development of an algorithm to calculate the loads on a component using stationary measurements can eliminate the need for rotating measurement equipment. The purpose is to predict the tail rotor power requirement of a helicopter throughout the mission profile by using the algorithm developed. The scope of this investigation was limited to representative flight regimes based upon a survey of Bell 206 jet rangers or OH-58A derivatives operators. Flight test data were collected at University of Tennessee Space Institute (UTSI). These data were then used to correlate with the results of the algorithm model. The model incorporated helicopter blade element theory, momentum theory, fin blockage effects, inertia effects, translational velocity effects, mechanical losses and altitude density correction. The model was executed using Microsoft Excel. The model required input data including helicopter characteristics, altitude, engine shaft horsepower, velocity. Based upon these data, the tail rotor power and pedal position were calculated. The calculation results of pedal position were compared with the flight test data. The accuracy of the tail rotor power was presented in the percentage of the maximum tail rotor power. It was found that the pedal position alone was a poor indicator of tail rotor power. The modeled elements mentioned above were included and resulted in significant improvement. Based on the calculated results, this model and measured pedal positions can provide at least 90-% confidence of the tail rotor power, except at large sideslip angles. Additionally, due to the tail rotor power sensitivity to the pedal position variations, the measurement of pedal positions should be performed precisely. Based on the results of this investigation, utilizing the algorithm model for predicting tail rotor power from pedal position will result in a 90-% confidence of the tail rotor power being applied. Recommend an alternative fuselage yaw moment due to sideslip chart be used to improve sideslip data. Recommend instrumented tail rotor for tail rotor power measurements.
Download or read book Aeronautical Engineering written by and published by . This book was released on 1975 with total page 586 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Download or read book Introduction to autogyros helicopters and other V STOL aircraft written by Franklin D. Harris and published by . This book was released on 2011 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Helicopter Maintenance written by Joseph Schafer and published by . This book was released on 2019-08 with total page 360 pages. Available in PDF, EPUB and Kindle. Book excerpt:
