Areas for the standard metric series of thread diameter-pitch combinations for aerospace externally threaded fasteners are established for the following conditions: a) Area for ultimate shear stress or load in unthreaded shank. b) Area for ultimate tensile stress or load in thread. c) Area for stress durability test load in thread. d) Area for stress-rupture test load at elevated temperature. e) Area for tension-tension fatigue test load.
To establish the acceptance criteria for discontinuities as revealed by magnetic particle or liquid penetrant examination of aircraft utility parts as in 1.2.
To establish the acceptance criteria for discontinuities as revealed by magnetic particle or liquid penetrant examination of aircraft utility parts as in 1.2.
This standard establishes the acceptance criteria for surface discontinuities as revealed by magnetic particle or liquid penetrant examination of nuts.
This Aeronautical Recommended Practice provides a standard method for locating and dimensioning the airfoil portions of parts such as blades, and vanes. This method will apply to blades, or vanes with or without a base. The forms of attachment are varied; therefore, the blade bases shown in the following figures are for illustration only. All dimensions and notes shown pertaining to the common functional point, line or plane are considered to be applied to a datum, on or off the part, irrespective of the form of attachment.
This procurement specification covers rivets made from an aluminum alloy designated as 2117-T4, solution treated. The following specification designations and their rivet coatings are covered:
This standard specifies the areas to be used in calculating stress or load values to be used in externally and internally threaded fastener procurement specifications for bolts, screws, nuts, and studs and for the information of designers.
This standard specifies the areas to be used in calculating stress or load values for use in externally and internally threaded fastener procurement specifications for bolts, nuts, and studs and for the information of designers.
Areas for the standard metric series of thread diameter-pitch combinations for aerospace externally threaded fasteners are established for the following conditions: a Area for ultimate shear stress or load in unthreaded shank. b Area for ultimate tensile stress or load in thread. c Area for stress durability test load in thread. d Area for stress-rupture test load at elevated temperature. e Area for tension-tension fatigue test load.
Areas for the standard metric series of thread diameter-pitch combinations for aerospace externally threaded fasteners are established for the following conditions: a Area for ultimate shear stress or load in unthreaded shank. b Area for ultimate tensile stress or load in thread. c Area for stress durability test load in thread. d Area for stress-rupture test load at elevated temperature. e Area for tension-tension fatigue test load.