MIL-PRF-85676A(AS)
2.3 Order of precedence. In the event of a conflict between the text of this document and
the references cited herein, the text of this document takes precedence. Nothing in this
document, however, supersedes applicable laws and regulations unless a specific exemption has
been obtained.
3. REQUIREMENTS.
3.1 Fixed and rotary wing emergency egress lighting system description. The fixed wing
and rotary wing emergency egress lighting subassembly shall provide illumination of an aircraft
emergency exit to enable rapid location of the exit by crewmembers and passengers inside the
aircraft in the event of a crash or emergency landing on land or at sea when the visibility is
reduced in the cabin compartment. The fixed wing requirements shall be applicable to lighter-
than-air aircraft. The rotary wing requirements shall be applicable to tilt-rotor aircraft. Other
aircraft configured to carry only passengers, shall include both requirements. The lighting
subassembly shall consist of those components necessary to illuminate designated emergency
escape exit(s). The lighting subassembly shall be comprised of light element(s), a control unit
with integral power source, cabling, connectors, and mounting hardware. Each lighting
subassembly shall operate independently of any other lighting subassembly. However, fixed
wing emergency lighting and main lighting systems may share the same source of general cabin
illumination. The power supply of the emergency lighting system shall be independent of the
main lighting system power supply. The fixed wing emergency lighting system shall also
include: Sources of general cabin illumination, interior lighting in emergency exit areas, and
floor proximity escape path marking.
3.1.1 Single & multiple light element subassemblies. A single light element
subassembly shall be comprised of one light element and a control unit. A multiple light element
subassembly shall be comprised of multiple light elements and a control unit.
3.2 First article. When specified (see 6.2), a sample shall be subjected to first article
inspection in accordance with 4.3.
3.3 Light element performance. The light element shall provide illumination during
preflight check. The peak chromaticity (relative spectral radiance) of the light elements shall be
within a range of 510-575 nanometers. The amount of light energy in the 600-900 nanometer
range shall be compatible with the operating characteristics of all in-service night vision goggles.
3.3.1 Rotary wing and tilt-rotor aircraft. The luminance of each light element throughout
the duration of operation specified in 3.3 shall be a minimum of 42 foot-lamberts for a projected
one-half-inch minimum visible width from any viewing angle within ± 65° of normal. Once
actuated, light element output shall be continuous (See 6.3).
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