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|  MIL-81752A(AS)
3.8.1 General - The design of the system shall conform to the
requirements of MIL-STD-1472.
3.8.2 Safety - The windshield system shall be designed to
preclude the incorporation of features which result in catastrophic
hazards as specified in MIL-STD-882.
3.8.3 Cockpit space - The windshield system design shall provide
adequate space In the cockpit for personnel and equipment specified in
the detail specification for the airplane. There shall be no sharp
corners or projections into the cockpit which might result in injury
to the pilot during a crash.
3.8.4 Eye location envelope - The pilot's design eye position
shall be located in accordance with the proposed cockpit geometry
specified in the detail specification for the airplane. The envelope
of permissible eye travel shall be as specified in the detail
specification for the airplane and shall comply with MIL-STD-1333.
3.8.5 Vision
3.8.5.1 Envelope - The windshield, as part of the cockpit
enclosure, shall be designed to provide vision from the cockpit as
required by MIL-STD-850, as a minimum.
3.8.5.2 Tandem cockpit - For aircraft utilizing a tandem cockpit
arrangement in which the pilot may occupy the rear cockpit, the vision
If forward vision is limited by the
requirements of 3.8.5.1 apply.
person and seat in the front cockpit, effect of such obstruction shall
be kept to an absolute minimum and shall be demonstrated by a mockup.
3.8.5.3 Night Vision Goggle (NVG) compatibility - When specified
in the detail specifcation for the aircraft, the windshield shall be
NVG compatible over the wavelength range of 600 to 900 nanometers.
3.8.5.4 Primary viewing zone - Zone I shall be considered the
primary operational viewing zone of the windshield used by the pilot.
Zone I definition dimensions shall be submitted to the procuring
activity for approval (See 6.3.1).
3.8.6 Optics
3.8.6.1 General - The windshield shall be capable of meeting the
optical requirements specified in 3.8.6 before and after a minimum of
two lifetimes of pressure/temperature cycling as specified in the
aircraft detail specification.
3.8.6.2 Luminous
transmittance
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