MIL-PRF-85676A(AS)
3.4.3 Mounting features. Provisions for mounting to a structural member shall allow for
removal and replacement of the light assembly.
3.4.4 Light element configuration. Design of the light element shall be such that failure
of a point light source shall not result in the failure of any other point light source within the light
element.
3.5 Functional characteristics.
3.5.1 Rotary wing and tilt-rotor aircraft. The lighting subassembly shall be designed for
use in emergency situations only. The lighting subassembly shall provide illumination at or
above minimum levels as required for not less than10 minutes within one second subsequent to
initiation. The lighting assembly shall operate in air or while submerged in fresh or seawater to a
depth of 50 feet and shall be deactivated prior to flight in the case of a "lights-out" nighttime
mission requirement.
3.5.2 Fixed wing and lighter-than-air aircraft. Emergency illumination shall be
maintained at or above the minimum level for not less than 10 minutes at critical ambient
conditions after an emergency landing on land or water and shall operate in air or while
submerged in fresh or seawater. The lighting assembly shall operate in air or while submerged
in fresh or seawater to a depth of 50 feet and shall be deactivated prior to flight in the case of a
"lights-out" nighttime mission requirement (see 6.12.1).
3.5.3 Aircraft configured to carry only passengers. The functional characteristics of the
EEL configured to carry only passengers shall conform to 3.5.1 and 3.5.2.
3.6 Control unit.
3.6.1 Control unit performance. The control unit shall include a status indicator which
provides a visual means to verify that the power source is sufficient for the lighting subassembly
to meet the performance requirements of 3.5 and the operational status of each lighting
subassembly (function and disable).
3.6.1.1 Rotary wing and tilt rotor aircraft. The control unit for the lighting subassembly
shall provide interface for the light element(s). The control assembly shall also provide power,
activation and control logic, status indications, test capability and, if applicable, power source
charging control for the lighting subassembly.
3.6.1.2 Fixed wing and lighter-than-air aircraft. The emergency lighting system shall
provide for manual operation of the lights from the flight crew station and from a location in the
passenger compartment that is within reach of an operator seated in an assigned seat. Emergency
lighting in the flight deck shall be arranged so as to minimize glare and problems with dark
adaptation by the flight crew. There shall be a flight crew warning light that illuminates when
main aircraft power is on in the aircraft and the emergency lighting system is not ARMED (see
6.9).
3.6.1.2.1 Cockpit control device. The cockpit control device shall have ON, OFF, and
ARMED positions and have means to safeguard against inadvertent operation of the control
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