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|  MIL-G-85103B(AS)
a provision neutralizing the transfer unit at any time the gun is being removed
or is being installed.
3.3.5.5.1 Safety during nongunnery missions. A positive means shall be
provided to isolate the gun system from the aircraft control inputs in order to
prevent gun firing during nongunnery missions.
3.3.5.6 Gun gas ventilation. The gun system shall provide sufficient
ventilation to prevent accumulation of gun gas concentration which may result in a
gun gas explosion when installed on the aircraft throughout the flight envelope
of Figure 3, and during ground firing with the access doors open.
3.3.6 Human performance/human engineering. The gun system design shall
consider and apply the principles, analyses, criteria, and philosophies of human
engineering as defined in MIL-STD-1472. This shall include the knowledge of
man's unique capabilities and limitations regarding the installation, operation$
and maintenance of the gun system.
3.3.7 Pneumatic system construction. The gun system pneumatic system shall
be designed, constructed, and meet all applicable requirements in accordance
with MIL-P-8564, Type I and MIL-P-5518, Type B, Class 2.
3.3.8 Hydraulic system construction. The gun system hydraulic system shall
be designed, constructed, installed, and meet all applicable requirements in
accordance with MIL-H-5440, Type I, Class 3000. Hydraulic fluid shall meet the
requirements of MIL-H-83282.
3.3.9 Electrical system construction. The gun system electrical system
shall be designed, constructed, and shall have workmanship to meet all applicable
requirements of MIL-E-5400 for Class 1 equipment.
3.3.10 Structural capability.
3.3.10.1 Crash survivability limit loads. The gun assembly (structural
attach points, mounting means, and mechanical interface) shall have crash
survivability limit load of at least 20 g in a 20 degree forward longitudinal
cone, and 12 g vertically and laterally.
3.3.10.2 Limit loads. Critical load factors for design consideration shall
be as specified below:
nz (vertical) +8.0g
-3.0g
ny (lateral) 1.5g
nx (longitudinal) 3.5g forward (aircraft braking)
1.5g aft (aircraft accelerating)
Aircraft roll rate: 270 degrees per second maximim
Aircraft roll acceleration: 18 radians per second squared
Aircraft roll acceleration: +6 radians per second squared
18
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