| Flight Test Techniques |
01-Jul-2009 |
33 pages |
| Authors:
ARMY AVIATION TECHNICAL TEST CENTER FORT RUCKER AL
|
 | This TOP provides an overarching compilation of flight test techniques used in the conduct of both fixed- and rotary-wing aircraft. These techniques include procedures for conducting handling qualities and performance flight tests. Classical flight test techniques are taught at the recognized test pilot schools. Many Flight Test Manuals are available to document these tests and test techniques and are referenced in this TOP to provide a single source for currently ... |
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| Performance of the Communication Enhancement and Protective System (CEPS) Under Sustained High and Low Temperatures |
01-May-2008 |
30 pages |
| Authors:
Elmaree Gordon; Adrianus J Houtsma; ARMY AEROMEDICAL RESEARCH LAB FORT RUCKER AL
|
| The USAARL conducted airworthiness testing on the Communication Enhancement and Protection System (CEPS). The test plan included conducting acoustic performance evaluations of the CEPS to determine if the CEPS would maintains clear and audible communications to the ear of the user and all its components would remain operational after exposure to sustained high and low temperatures conditions (Department of Defense Test Method Standard for Environmental Engineering Considerations and Laboratory Tests ... |
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| Testing of 7050-T7451 Aluminum Strain-Life Coupons for a Probabilistic Strain-Life Curve |
02 NOV 2006 |
69 pages |
| Authors:
David T. Rusk; Robert E. Taylor; Paul C. Hoffman; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD
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| Fleet life tracking is an integral part of NAVAIR s approach to ensuring the airworthiness and operational readiness of U.S. Naval Aviation assets. Historically, life limits for Naval airframe components have been derived by deterministic analyses of stress-life or strain-life fatigue models. To improve fatigue life prediction capabilities for airframe structures, NAVAIR has begun development of a Probabilistic Strain-Life model. As a first step in the development of the Probabilistic ... |
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| Estimating the Distribution of the Sizes Of Flaws Remaining After an Inspection (Preprint) |
SEP 2006 |
11 pages |
| Authors:
Peter W. Hovey; Alan P. Berens; Jeremy Knopp; DAYTON UNIV OH DEPT OF MATHEMATICS
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| The U.S. Air Force plans for maintenance and retirement of aircraft based in part on fatigue crack growth models. Periodic inspections are used to help assess airworthiness and plan for future inspections. Nondestructive inspections are not perfect so some cracks are missed and the likelihood that an individual crack is detected is a function of the size of the crack when inspected. Additionally, the crack size distribution is related to ... |
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| Air Vehicles Division Computational Structural Analysis Facilities Policy and Guidelines for Users |
28 SEP 2005 |
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| Authors:
S. Sanderson; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION VICTORIA (AUSTRALIA) PLATFORM SCIENCES LAB
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 | This document presents the operating policies and guidelines for the use of the Computational Structural Analysis Facilities (CSAF) within Air Vehicles Division (AVD). It has been created to assist users of the CSAF to perform professional, high quality finite element analysis (FEA). FE analysts from many tasks within AVD are using the facilities to conduct FEA with respect to the assessment of structural integrity and technical airworthiness of ADF aircraft. ... |
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| DEF STAN 00-970 Requirements for the Design and Airworthiness of Composite Aircraft Structure |
JUN 2003 |
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| Authors:
Paul J. Callus; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION VICTORIA (AUSTRALIA) PLATFORM SCIENCES LAB
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| One of the impediments to the introduction of composite structure into Australian Defence Force (ADF) aircraft is the difficulty in identifying those airworthiness requirements specific to these materials. The ADF uses a comparative approach where tenderers propose their own certification basis. This is assessed against the ADF comparative certification basis to ensure that all relevant issues are covered in adequate depth. The ADF comparative certification basis is DEF STAN 00-970 ... |
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| Third International Conference on Health and Usage Monitoring - HUMS2003 |
FEB 2003 |
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| Authors:
Graham F. Forsyth; DEPARTMENT OF DEFENCE CANBERRA (AUSTRALIA)
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| This document includes formal papers for the Third International Conference on Health and Usage Monitoring, HUMS2003, which will be held in Melbourne in February 2003. The scope of papers covers a wide range of monitoring issues with focus on the application to helicopters, military aircraft and gas turbine engines This document includes only the formal papers made available for publication during December 2002. Other papers will be available from the ... |
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| Airworthiness Qualification Criteria for Rotorcraft with External Sling Loads |
JAN 2002 |
36 pages |
| Authors:
David L. Key; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER
|
| This report presents the results of a study to develop airworthiness requirements for rotorcraft with external sling loads. The report starts with a review of the various phenomena that limit external sling load operations. Specifically discussed are the rotorcraft-load aeroservoelastic stability, load- on handling qualities, effects of automatic flight control system failure, load suspension system failure, and load stability at speed. Based on past experience and treatment of these phenomena, ... |
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| Impact of Parameter Accuracy on Aircraft Structural Integrity Estimates |
JUL 2001 |
177 pages |
| Authors:
Scott A. Fawaz; James A. Harter; AIR FORCE ACADEMY COLORADO SPRINGS CO
|
| This report docments work performed to quantify the effect of various Linear Elastic Fracture Mechanics (LEFM) parameters and material properties on the life of aircraft structures. Automated computer methods were used to perform life comparisons using the Air Force crack growth life prediction software, AFGROW. |
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| Aircraft Certification Systems Evaluation Program (ACSEP) FY 2000 |
29 MAY 2001 |
54 pages |
| Authors:
FEDERAL AVIATION ADMINISTRATION WASHINGTON DC OFFICE OF AVIATION RESEARCH
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| This report documents the fiscal year (FY) 2000 results of the Federal Aviation Administration (FAA) Aircraft Certification Service (AIR) aircraft Certification Systems Evaluation Program (ACSEP). The ACSEP was designed to determine if FAA production approval holders and delegated facilities are complying with the requirements of applicable Code of Federal Regulations (CFR) and the procedures established to meet those requirements. It also surveys the application of standardized industry practices, not required ... |
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| DSTO International Conference on Health and Usage Monitoring February 19-20, 2001 |
FEB 2001 |
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| Authors:
Graham F. Forsyth; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION CANBERRA (AUSTRALIA)
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| The concept of On-Condition Maintenance implies the need for Condition Monitoring to close the loop. Condition monitoring may be implemented at many levels requiring various degree of complication. As relatively fragile machines with catastrophic outcomes possible for many failure types, aircraft have always used some degree on monitoring. Recently, engines, mechanical systems and airframes on both fixed-wing aircraft and helicopters are being fitted with permanent monitoring systems. These systems are ... |
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| Aging Engines, Avionics, Subsystems and Helicopters |
01 OCT 2000 |
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| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
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| Aging Aircraft concerns have dramatically escalated in the military community and commercial aviation during the past decade. Some models, which have already been in service for more than 40 years, will need to be retained for another two decades or longer, often serving in roles and in theatres very different from what was envisioned when they were originally designed. Aging Aircraft has several connotations. To name a few: technological obsolescence, ... |
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| Experimental Investigations of Material Models for Ti-6Al-4V Titanium and 2024-T3 Aluminum |
SEP 2000 |
41 pages |
| Authors:
LAWRENCE LIVERMORE NATIONAL LAB CA
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| The report describes studies of the deformation and failure behavior of Ti-6Al-4V titanium and 2024-T3 aluminum. This work was accomplished by the Lawrence Livermore National Laboratory under an Interagency Agreement between the Federal Aviation Administration (FAA) William J. Hughes Technical Center and the Department of Energy (DOE). The work was accomplished under the FAA's Aircraft Catastrophic Failure Prevention Program as part of its research into ... |
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| Corrosion and Corrosion Fatigue of Airframe Materials |
JUL 2000 |
79 pages |
| Authors:
Robert P. Wei; LEHIGH UNIV BETHLEHEM PA DEPT OF MECHANICAL ENGINEERING AND MECHANICS
|
| This report summarizes research performed under Grant 92-G-0006 and complementary programs sponsored by the Air Force Office of Scientific Research under Grants F49620-96-1-0245 and F49620-9g-1-0198. The objectives of these programs are (1) the development of a basic understanding of the processes of localized corrosion and corrosion fatigue crack nucleation and growth in high strength aluminum alloys used in airframe construction, (2) the formulation of ... |
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| Application of Damage Tolerance Principles for Improved Airworthiness of Rotorcraft (l'Application des principes de la tolerance a l'endommagement pour une meilleure aptitude au vol des aeronefs a voilure tournante) |
FEB 2000 |
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| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
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| The Specialists' Meeting dealt with Aging Systems and more specifically Application of Damage Tolerance Principles for Improved Airworthiness of Rotorcraft. These proceedings include a Keynote Address and fifteen papers having the objective of discussing and presenting the applicability of the new design approach to major rotorcraft components such as the dynamic system, primary load carrying structures and flight control systems. Both metal and composite structures including special material related topics ... |
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| Modeling and Simulation Support for the Operational Test and Evaluation of a Tactical Airborne Reconnaissance System |
DEC 1999 |
179 pages |
| Authors:
Kevin J. Schmidt; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| Today's decreasing defense budget has forced the military to reduce its spending on operational testing of new equipment, among many other areas. Reduced testing has forced evaluators to focus their attention on possible sensitive issues prior to and during testing of new equipment. The Simulation, Test, and Evaluation Process implemented in 1995 to help reduce testing costs has been an integral part of the test ... |
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| Design and Airworthiness Requirements for Military Unmanned Air Vehicle Systems |
SEP 1999 |
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| Authors:
Bernard C. Rogers; DEFENCE PROCUREMENT AGENCY BRISTOL (UNITED KINGDOM)
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| This paper examines the safety implications and factors to be considered for the procurement of a UAV and identifies the design requirements to be used as a guide to produce an air vehicle specification. It will touch on matters covered in more detail by other presenters because of the need to reflect the information they provide within the new standard. It should be noted that while appreciating that dirigibles and ... |
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| Workshop on Helicopter Health and Usage Monitoring Systems, Melbourne, Australia, Part 2 |
FEB 1999 |
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| Authors:
Graham F. Forsyth; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION CANBERRA (AUSTRALIA)
|
| Over the last 10 years, helicopter Health and Usage Monitoring Systems (HUMS) have moved from the research environment to being viable systems for fitment to civil and military helicopters. In the civil environment, the situation has reached the point where it has become a mandatory requirement for some classes of helicopters to have HUMS fitted. Military operators have lagged their civil counterparts in implementing HUMS, but that situation appears set ... |
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| Nanoflyer |
13 OCT 97 |
12 pages |
| Authors:
J. Katz; R. Garwin; W. Press; MITRE CORP MCLEAN VA JASON PROGRAM OFFICE
|
| A recent proposal to use electrostatic forces to lift and propel a small airborne vehicle is examined. We show here that although this is permitted by the laws of physics, it is very inefficient, and is limited to low areal loads by the requirement to avoid electric breakdown. Electrostatic propulsion offers no special advantages which might justify the price of its inefficiency. |
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| T56 Propulsion System Cost Study |
NOV 96 |
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| Authors:
Kevin M. Jaansalu; Robert R. Hastings; Greg N. Nelson; DEFENCE AND CIVIL INST OF ENVIRONMENTAL MEDICINE DOWNSVIEW (ONTARIO)
|
| This study analyzes operating costs and flight safety data of the propulsion systems on the CC-130 Hercules and CP-140 Aurora/Arcturus aircraft to identify where R&D investment could provide airworthiness or program cost benefits. Operational impact and R&O cost data are provided on the gas turbine engine, the reduction gearbox, and the propeller systems. The propeller system has a greater impact for both aircraft types on flight safety occurrences than the ... |
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| Airworthiness Qualification Test Directorate (AQTD). Bibliography: (Author/Report/Aircraft) 1961-1995 |
JAN 96 |
298 pages |
| Authors:
Shelia Benner; ARMY AVIATION TECHNICAL TEST CENTER EDWARDS AFB CA
|
| The mission of the Airworthiness Qualification Test Directorate (AQTD) (previously known as the U.S. Army Aviation Engineering Flight Activity (AEFA)) of the U.S. Army Aviation Technical Test Center, is to conduct airworthiness qualification fight tests of air vehicles developed and/or procured as integrated systems and airworthiness evaluations of those vehicles proposed or considered for Army application or which incorporate advanced concepts having potential military application; produce test data on basic ... |
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| AGM-154 Joint Standoff Weapon |
12 APR 95 |
21 pages |
| Authors:
Dan Hinson; Mike Griffith; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD
|
| JSOW stands for 'Joint Standoff Weapon'. It was designed to be on affordable air-delivered stand-off weapon that is capable against fixed, relocatable and moving targets. It can be used during day, night altitude launch capability from outside target point defenses. The JSOW will maximize interoperability and affordability through system commonality with USMC and USAF platforms. All variants of the JSOW will be all-up rounds (AUR), using common equipment when possible. ... |
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| Airworthiness Testing of Fixed Wing Aircraft (Asymmetric Power Testing) |
23 DEC 94 |
17 pages |
| Authors:
ARMY AVIATION TECHNICAL TEST CENTER FORT RUCKER AL
|
| This TOP establishes procedures and methods for evaluating the asymmetric power handling qualities of multi-engine fixed-wing aircraft during developmental testing. This TOP is limited to handling qualities only and does not address aircraft performance. |
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| AGARD Flight Test Techniques Series. Volume 12. The Principles of Flight Test Assessment of Flight-Safety-Critical Systems in Helicopters (Les Principes de l'Evaluation, dans le Cadre des Essais en Vol, des Systemes Indispensables a la Securite de Vol des |
AUG 1994 |
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| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
| Modern helicopters usually incorporate many engineering systems (including pilot aiding systems such as autostabilisers and flight directors) which are essential to the safe and effective use of the helicopter. Where the helicopter can be endangered by failure of a system (or of one of its units), that system is termed flight safety critical. In general, the use of those systems should not incur a higher probability of hazard to the ... |
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| An Assessment of Fatigue Damage and Crack Growth Prediction Techniques (L'Evaluation de l'Endommagement en Fatigue et les Techniques de Prediction de la Propagation des Fissures) |
MAR 94 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
|
| The Workshop provided a forum for an in-depth discussion of the correlation between in-service experience and results from analytical predictive models, specimen level tests, component tests and full-scale tests. Additionally, the Workshop made possible an examination of the operating standards that different countries adopt with respect to various elements in the design process such as load spectrum, exceedance diagram algorithm for calculating fatigue damage, and in-service monitoring protocol-all contributing to ... |
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| Analysis Concerning the Inspection Threshold for Multi-Site Damage. |
DEC 1993 |
50 pages |
| Authors:
David Broek; FRACTURESEARCH INC GALENA OH
|
| Periodic inspections, at a prescribed interval, for Multi-Site Damage (MSD) in longitudinal fuselage lap-joints start when the aircraft has accumulated a certain number of flights, the inspection threshold. The work reported here was an attempt to obtain justification for the threshold. It is based upon an analysis of fatigue data for lap-joints (riveted as well as riveted plus bonded) of a configuration closely resembling those in several types of aircraft. ... |
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| Full-Scale Testing and Analysis of Curved Aircraft Fuselage Panels |
DEC 93 |
58 pages |
| Authors:
G. Samavedam; D. Hoadley; D. Thomson; FOSTER-MILLER INC WALTHAM MA
|
| This report presents data on (1) residual strength of aircraft panels containing Multiple-Site Damage (MSD) in tap splices, and (2) fatigue strength of panels subjected to cyclic pressure loading. The testing was conducted using the dedicated Aging Aircraft Test Facility previously built in the Foster-Miller laboratory. A previous report describes the work in the first phase involving the design and operation of the facility and the test data generated on ... |
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| Reliability Assessment at Airline Inspection Facilities. Volume 1. A generic Protocol for Inspection Reliability Experiments. Volume 1 |
MAR 93 |
34 pages |
| Authors:
Floyd Spencer; Giancarlo Borgonovi; Dennis Roach; Don Schurman; Ron Smith; SANDIA NATIONAL LABS ALBUQUERQUE NM
|
| Volume I is the first document is a series of three describing the planning, execution, and results of an eddy current inspection field experiment. This document defines a generic protocol for inspection reliability experiments. It contains an introduction to the currently accepted forms of data analysis and presentation (Probability of Detection and Receiver Operating Characteristic curves) and a discussion of the factors that may affect inspection reliability. |
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| Preliminary Airworthiness Evaluation of the Woodward Hydromechanical Unit Installed on T700-GE-700 Engines in the UH-60A Helicopter |
AUG 89 |
56 pages |
| Authors:
Joseph L. Piotrowski; Christopher J. Young; Thomas P. Walsh; Julie Sandman; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The U.S. Army Aviation Engineering Flight Activity conducted a Prelimiary Airworthiness Evaluation of the Woodward Hydromechanical Unit (HMU) installed on T700-GE-700 engines in the UH-60A helicopter from 14 May 1989 to 14 June 1989. The evaluation was conducted at Edwards AFB, California (elevation 2302 feet) and Coyote Flat, California (elevation 9980 feet) on aircraft S/N 88- 26015. The evaluation consisted of eleven flights for a total of 15.5 productive flight ... |
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| Airworthiness and Flight Characteristics Evaluation of the McDonnell Douglas Helicopter Corporation (MDHC) 530FF Helicopter |
MAY 89 |
299 pages |
| Authors:
James L. Webre; William Y. Abbott; Michael White; William Stormer; Warren Gould; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| An Airworthiness and Flight Characteristics Evaluation of the McDonnell Douglas 530FF helicopter (also known as the AH-6G or MH-6H) was performed by the U.S. Army Aviation Engineering Flight Activity between August 1987 and September 1988. The test consumed 94 productive flight test hours in 152 total hours. Many configurations were flown at gross weights up to 3950 pounds. Three deficiencies related to the handling qualities, and one related to the ... |
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| Castings Airworthiness |
MAY 89 |
|
| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
|
| The AGARD Structures and Materials Panel held a Workshop on Castings Airworthiness in Mierlo, Netherlands in the Fall of 1988 to consider whether a casting factor, as such need still be applied to premium quality castings given the improvements in casting technology obtained in recent years. A first series of papers addressing this question was presented by airworthiness officials, both military and civil, of the NATO nations. In a second, ... |
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| U. S. Army Aviation Engineering Flight Activity (AEFA) Report Bibliography, Management Cost Performance Within the Corps of Engineers |
APR 89 |
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| Authors:
Sheila Lewis; Maryanna Lake; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The mission of the U.S. Army Aviation Engineering Flight Activ ity (AEFA) is to conduct airworthiness qualification flight tests of air vehicles developed and/or procured as integrated systems and airworthiness evaluations of those vehicles proposed or considered for Army application or which incorporate advanced concepts having potential military application; produce test data on basic air vehicle performance, handling qualities, system/subsystem interface, and integrated system performance; and conduct a test pilot ... |
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| Preliminary Airworthiness Evaluation of the AH-64A Equipped with the Air to Air Stinger (ATAS) Missile System |
DEC 88 |
118 pages |
| Authors:
John S. Lawrence; Joseph A. Lyle; Gerald J. Hopkins; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| A Preliminary Airworthiness Evaluation was conducted for the AH-64A equipped with the Air-to-Air Stinger (ATAS) missile system. The first phase was an evaluation of the effects of the ATAS installation on the handling qualities on the AH-64A. The second phase was a human factors evaluation of the installation of a fully operational preproduction ATAS system using captive flight training Stinger missiles, Tests were flown in the eight Hellfire missile configuration. ... |
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| Preliminary Airworthiness Evaluation of the UH-60A External Fuel System |
DEC 88 |
|
| Authors:
Michael K. Herbst; Michael A. Gleason; Paul Losier; Reginald C. Murrell; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| Testing was conducted to determine the effects of the installation of the External Fuel System (EFS) on the performance and handling qualities of the UH-60A helicopter. A total of 27 productive flight hours were flown at Edwards Air Force Base, California between 21 March and 20 May 1988. The evaluation did not reveal any problems that should preclude airworthiness qualification. The installation of the EFS with two 230-gallon tanks caused ... |
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| Airworthiness and Flight Characteristics Evaluation of the EH-60A (Quick Fix) Helicopter |
OCT 88 |
98 pages |
| Authors:
David B. Cripps; Donald L. Underwood; David A. Downey; George M. Yamakawa; Charles Q. Crowell; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The U.S. Army Aviation Engineering Flight Activity conducted a limited Airworthiness and Flight Characteristics test of the EH-60A (Quick Fix) helicopter. During the test program, 49 flights were conducted for a total of 63.5 hours, of which 47.1 were productive. Initially the EH-60A was modified to the utility configuration where 22.3 productive hours were flown airspeed calibration, level flight performance, and vibration characteristics. All tests were performed at a Quick ... |
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| Preliminary Airworthiness Evaluation of the RC-12H Airplane |
OCT 87 |
73 pages |
| Authors:
Joseph C. Miess; Reginald C. Murrell; Robert M. Buckanin; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The objective of this PAE was to conduct a limited quantitative performance and handling qualities evaluation of the RC-12H to determine the effects of the sensor pod and antenna configuration on performance and handling qualities. The RC-12H (GUARDRAIL/COMMON SENSOR) is an RC-12D aircraft which has been modified to accommodate larger direction finder/electronic intelligence (DF/ELINT) pods on each wing tip and the communications high accuracy airborne location syste. The RC-12H manufactured ... |
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| Airworthiness and Flight Characteristics Test of a Ski Assembly for the UH-60A Black Hawk Helicopter |
AUG 87 |
127 pages |
| Authors:
Randall W. Cason; John I. Nagata; Thomas L. Reynolds; Daumants Belte; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| An Airworthiness and Flight Characteristics test of the UH-60A helicopter (S/N 84-23953) configured with a ski assembly was conducted by the U. S. Army Aviation Engineering Flight Activity. The test was conducted at the Sikorsky Flight Test Facility at West Palm Beach, Florida (elevation 28 feet). A total of 25.5 productive flight hours were flown during the period 6 to 30 April 1987. Tests were conducted to determine the handling ... |
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| Flight Worthiness of Fire Resistant Hydraulic Systems. Volume 2. Component and Endurance Testing |
30 DEC 86 |
|
| Authors:
J. R. Jeffery; S. E. Pehowski; N. J. Pierce; J. A. Wieldt; R. E. Young; MCDONNELL AIRCRAFT CORP ST LOUIS MO
|
| This document is the second of two volumes which make up the Flight Worthiness of Fire Resistant Hydraulic Systems final report. This document reports efforts involved in component procurement, analysis, qualification testing, the 750-hour endurance test, analytical model verification, and results of the teardown are included. The follow-on contract to perform a study of pump pulsation attenuation and actuator stiffness are reported in this volume. Components procured for the endurance ... |
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| Airworthiness and Flight Characteristics Test (A&FC) of the BHTI (Bell Helicopter Textron, Inc.) 214ST Helicopter |
FEB 86 |
|
| Authors:
Robert A. Williams; Randall W. Cason; Robert M. Buckanin; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| 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 ... |
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| Flight Worthiness of Fire Resistant Hydraulic Systems. Volume 1 |
DEC 1984 |
|
| Authors:
J. R. Jeffery; R. B. Merrell; N. J. Pierce; M. J. Stevens; R. E. Young; MCDONNELL AIRCRAFT CO ST LOUIS MO
|
| This volume reports a study to select a flight worthy hydraulic system in which to test the chlorotrifluoroethylene (CTFE) hydraulic fluid. Aircraft selection, hardware and concept definition, system and weight analysis, and reliability, maintainability and life cycles costs (LCC) studies are reported in volume I. The F-15 and KC-10A were selected for comparison between the present fluid and system configuraation and CTFE fluid at 8,000 psi plus various energy conservation ... |
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| Preliminary Airworthiness Evaluation of the Rutan Aircraft Factory (RAF) , Inc. LONG-EZ Airplane with External Sight |
MAY 1984 |
|
| Authors:
D. L. Underwood; G. M. Yamakawa; T. L. Reynolds; W. F. Carmona; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The US Army Aviation Engineering Flight Activity conducted a Preliminary Airworthiness Evaluation of the LONG-EZ airplane with an external sensor (Combat Surveillance Airborne Test Bed (CSATB) configuration). During the test program 13 flights were conducted for a total of 15.3 hours, of which 11.6 were productive. The objectives of the evaluation were to assess the performance and handling qualities of the LONG-EZ so that the US Army Aviation systems Command ... |
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| Airworthiness and Flight Characteristics Test of the OH-6A Configured to a Light Combat Helicopter (JOH-6A LCH) |
NOV 83 |
|
| Authors:
James L. Webre; Ralph Woratschek; Eric L. Mitchell; Richard S. Adler; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| Limited airworthiness and flight characteristics test of the JOH-6A Light Combat Helicopter (LCH) were conducted. The JOH-6A LCH configuration increased mission gross weight to 2700 pounds and includes one 7-tube 2.75 inch rocket pod and one 7.62 mm minigun mounted externally. Performance and handling qualities were evaluated at test sites from near sea level (488 feet) to 9980 feet. A total of 44 flights were conducted requiring 34.6 productive flight ... |
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| Preliminary Airworthiness Evaluation of the OH-58C with 3-Axis Stability Control Augmentation System and Improved Tail Rotor System |
OCT 83 |
|
| Authors:
M. L. Hanks; L. L. Todd; J. I. Nagata; M. S. Graham; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| This preliminary airworthiness evaluation was conducted on an OH-58C helicopter configured with a 3-axis digital stability control augmentation system (SCAS) and an improved tail rotor. Additional testing on the standard OH- 58C equipped with the 3-axis SCAS was required in response to questions which surfaced during working sessions of the Joint Special Study Group investigating 0H-58 loss of tail rotor effectiveness. Testing was accomplished at Arlington, TX (elevation 630 feet), ... |
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| The Civil Aircraft Airworthiness Data Recording Programme, |
OCT 1983 |
|
| Authors:
H. D. Ruben; CIVIL AVIATION AUTHORITY REDHILL (ENGLAND) AIRWORTHINESS DIV
|
| The idea of operational flight data recording started with the continuous recording of just two parameters velocity V and normal acceleration g. The value of information gained from these simple recorders incouraged improved recorders and their development is traced up to the high capacity digital recorders available today. The data recording programme operated jointly by the CAA and the participating airlines has grown considerably over the 20 years of its ... |
|
| Rotorcraft Icing Technology - An Update, |
OCT 1983 |
|
| Authors:
R. Ward; H. W. Chambers; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| Flight testing of rotorcraft in natural icing conditions is essential to the US Army Airworthiness Qualification requirements and to the US Federal Aviation Administration certification requirements as well as to support research and development efforts. Complete qualification/certification under natural icing conditions only is very expensive in terms of time due to the limited availability of the required test conditions in the natural environment. Consequently, inflight icing facilities that can duplicate ... |
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| Preliminary Airworthiness Evaluation of UH-60A with an Improved Airspeed System |
APR 1983 |
|
| Authors:
M. L. Hanks; R. MacMullin; G. L. Skinner; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The United States Army Aviation Engineering Flight Activity supported a contractor engineering effort to correct the nose-down pitch-over during takeoff and the large, variable position error in the low-speed flight regime of the UH-60A (Black Hawk) helicopter. A Preliminary Airworthiness Evaluation was then conducted with the improved airspeed and stabilator systems in their final configuration as defined by the contractor. Handling qualities and airspeed system characteristics were evaluated for two ... |
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| Preliminary Airworthiness Evaluation of the UH-60A Configured with the External Stores Support System (ESSS) |
MAR 1983 |
88 pages |
| Authors:
Arthur R. Marshall; Randall G. Oliver; Robert M. Buckanin; Richard S. Adler; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
|
| The Preliminary Airworthiness Evaluation of the UH-60A helicopter configured with the External Stores Support System was conducted. A total of 26 test flights were conducted. Limited level flight performance tests were conducted to determine the change in drag of the UH-60A helicopter caused by three External Stores Support System configurations with various stores installed. An unexplained increase in power required was found between the Preliminary Airworthiness Evaluation test aircraft and ... |
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| Airworthiness and Flight Characteristics (A&FC) Test of YAH-64 Advanced Attack Helicopter, Prototype Qualification Test-Government (PQT-G). Part 3 and Production Validation Test-Government (PVT-G) for Handbook Verification |
OCT 1982 |
272 pages |
| Authors:
Bartholomew d. Picasso III; Gary T. Downs; Robert M. Buckanin; Michael K. Herbst; ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA
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| The Airworthiness and Flight Characteristics Test of the YAH-64 helicopter was conducted. Seventy flights and 70.4 productive hours were flown. Performance testing assessed the probability of meeting the production contract requirements and consisted of an evaluation of hover, takeoff, level flight, forward flight climb and autorotational descent performance. Handling qualities testing determined compliance with selected research and development contract requirements and included standard stability and control tests, an evaluation of ... |
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| Flying Qualities of Relaxed Static Stability Aircraft. Volume I. Flying Qualities Airworthiness Assessment and Flight Testing of Augmented Aircraft |
SEP 1982 |
95 pages |
| Authors:
Roger H. Hoh; David G. Mitchell; SYSTEMS TECHNOLOGY INC HAWTHORNE CA
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| Volume I of the report deals with airworthiness assessment and flying qualities evaluation of highly augmented aircraft covered by Parts 23 and 25 of the Federal Aviation Regulations. Particular emphasis has been placed on aircraft with relaxed static stability and on the use of active augmentation systems to achieve the minimum requirement for a level of safety in such aircraft. Significant modifications and expansion to the FAA Engineering Flight Test ... |
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| Flying Qualities of Relaxed Static Stability Aircraft. Volume II. Ramifications of Flight-Essential/Critical Heavily-Augmented Airplane Characteristics on Flying Qualities |
SEP 1982 |
125 pages |
| Authors:
Duane McRuer; Thomas T. Myers; SYSTEMS TECHNOLOGY INC HAWTHORNE CA
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| Volume I of the report deals with airworthiness assessment and flying qualities evaluation of highly augmented aircraft covered by Parts 23 and 25 of the Federal Aviation Regulations. Particular emphasis has been placed on aircraft with relaxed static stability and on the use of active augmentation systems to achieve the minimum requirement for a level of safety in such aircraft. Significant modifications and expansion to the FAA Engineering Flight Test ... |
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Reports by Keyword(s)
*AIRWORTHINESS
