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This document establishes techniques for validating that a mission store complies with the interface requirements contained in MIL-STD-1760 Revision D.

Cyclic corrosion and media contamination effects during inertia dynamometer testing on torque output, coefficient of friction, surface condition, for passenger cars and light duty trucks up to 4540 kg of Gross Vehicle Weight Rating.

This document describes a method for measuring deformations, and fragment distribution patterns during an impact between a soft or frangible projectile and a regular helispherical leading edge. The document describes the hardware, setup, and instrumentation required. In this test method a soft body projectile impacts a helispherical leading edge symmetric to the curvature and centric in the transversal direction. The ductile target is backup by a rigid adapter structure behind. The target must be sufficiently large so that the projectile flows around its curvature and induces an indentation. This test is intended for measuring the remaining plastic deformation of the target after the impact. The projectile breakup pattern data may also be captured during this test. The values stated in either SI units or inch-pound units are considered separate standards. The values stated in each system may not be exactly equivalent; therefore, each system must be considered as independent.

This document describes a method for measuring deformations from a normal impact between a soft or frangible projectile and clamped plate. The document describes the hardware, setup, and instrumentation required. In this test method a soft body projectile impacts a square ductile plate clamped on all four sides. This test is intended for measuring the remaining plastic deformation of the target after the impact.The values stated in either SI units or inch-pound units are considered separate standards. The values stated in each system may not be exactly equivalent; therefore, each system must be considered as independent. This standard does not address all of the safety concerns associated with its use. It is the responsibility of each user of this standard to ensure that any safety issues are properly addressed.

This document defines the Level 1 tests required for qualifying an artificial bird for certification testing of aircraft and aircraft engines. Level 1 refers to the lowest level of the test pyramid associated with the building block approach defined in the CMH-17 Composite Materials Handbook. The test pyramid consists of a sequence of 5 levels of testing, ranging from the most basic at the lowest level of the pyramid to the most complex at the apex. Typically the number of tests performed has an inverse relationship to the complexity of the tests. The building block approach is used for defining the tests required to qualify an artificial bird that would be accepted by regulatory agencies for certification testing of aircraft, including rotorcraft, fixed wing fuselages and engines, where bird strike testing is currently required. This document only describes the tests required for Level 1 of the test pyramid. Separate documents define the tests required at higher levels.

This specification covers one type of aluminum bronze in the form of rods, bars, forgings, and forging stock.

The report shows how the methodology of measurement uncertainty can usefully be applied to test programs in order to optimize resources and save money. In doing so, it stresses the importance of integrating the generation of the Defined Measurement Process into more conventional project management techniques to create a Test Plan that allows accurate estimation of resources and trouble-free execution of the actual test. Finally, the report describes the need for post-test review and the importance of recycling lessons learned for the next project.

The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.

The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.

This specification covers connector and cable accessory heat shrinkable, electrical insulating, molded components fabricated from various polymer based compositions. These components are intended for use as connector and cable accessory components to provide strain relief, electrical insulation, and environmental sealing.

This document has been formulated as a suggested guide in assisting EIA Engineering Department Panels and JEDEC Councils in cooperating with the Defense Department and other Federal agencies in the preparation of suggested reliability requirements for various types of electronic products as part of a program designed to enhance the reliability of defense and related equipment. The document is to be followed merely as a guide and is not intended to limit technical groups in the consideration of the factors to be taken into account in the development of reliability specifications for recommendation to the Government.

Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.

Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.

This specification covers a polytetrafluoroethylene resin in the form of extruded and sintered flexible tube reinforced with wire braid.

This specification covers polytetrafluoroethylene resin in the form of extruded and sintered flexible hose reinforced with wire braid.

This specification covers a polytetrafluoroethylene resin in the form of extruded and sintered flexible tube reinforced with wire braid.