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|  MIL-W-81752A(AS)
3.6.1 General - The windshield system shall be designed to
withstand the load Imposed by conditions specified in MIL-A-8860, in
the detail specification of the airplane, and as modified herein.
3.6,2 Load factors - All structural designs shall be in
accordance with MIL-A -8860, and the detail specification of the
Transparent windshields and associated structure shall be
airplane.
designed to ensure structural continuity and compatibility between
windshield and surrounding structure. Additional design load factors
shall be used as required to ensure safety. Deflections which may
cause glass breakage or stress crazing in plastic panels shall be
The size, contour, and material of the transparent
avoided.
windshield shall be considered in establishing a valid design load
factor.
3.6.3 Pressurization loads - The windshield system shall be
designed to withstand the pressurization loads specified in MIL-A-
The design shall include the effects of continuous and cyclic
8860.
pressurization loads, aerodynamic loads, and the effects of
temperature and temperature differentials throughout the ground and
flight envelope of the aircraft. In the event of cabin
overpressurization due to a failure in the pressurization control
system, the windshield system shall be designed to remain intact
beyond the point where pressure is relieved by failure or deflection
of some other less critical portion of the cockpit.
3.6.4 Airload distribution - The magnitude and distribution of
the airloads used in the structural design shall be those determined
by the use of acceptable analytic methods and reliable aerodynamic
data applicable to the conditions encompassed by the aircraft design
limit flight envelope. This data shall include, at a minimum, the
effects of math number, aeroelasticity, and thermal effects.
3.6.5 Landing arrestment barrier/barricade - The windshield
structure shall be designated to withstand loads imposed by contact with
arrestment barrier/barricade cables during emergency landing. No
failure shall be permitted which might result in injury to the pilot.
3.6.6 Crash and ditching - The windshield system design shall
guard against failures which sight result in injury to the pilot
during crash or ditching.
3.6.7 Underwater survival - When underwater escape provisions are
required by the detail specification for the airplane, the windshield
shall be designed such that excessive deflection or failure will not
prevent canopy or hatch opening.
3.7 Windshield
survivability
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