MIL-PRF-85676A(AS)
3.6.3.3 Aircraft configured to carry only passengers. The EEL system used in aircraft
that are configured to carry only passengers shall have means of activation that conform to 3.6.3,
3.6.3.1, and 3.6.3.2.
3.7 Reliability. The lighting subassembly shall be designed and constructed to meet or
exceed a reliability of 99.9 percent for a mission (see 6.12.3). Lighting subassembly failure shall
be defined as:
a. In the case of point light sources, the loss of capability to illuminate at least 90 percent
of the point light sources of each light element to meet the performance characteristics specified
in 3.5, such that no more than five point light sources per lighted linear foot are inoperable.
b. For continuous light sources, loss of illumination capability.
c. Inadvertent activation.
3.8 Maintainability.
3.8.1 Maintainability design. The lighting subassembly shall be designed to achieve at
least the following maintainability levels:
a. The mean time to repair (MTTR) of the lighting subassembly at the organizational
maintenance level shall be not greater than 15 minutes. Ninety percent of all corrective
maintenance actions shall be accomplished within 30 minutes, excluding administrative and
logistics delay time.
b. The direct maintenance man-hours per flight hour (DMMH/FH) at the organizational
level for preventive and corrective maintenance shall be not greater than 0.0025.
3.8.2 Maintenance concept. Non-emergency operation of the subassembly during its
service life shall be limited to the performance of go/no-go power source checks at the
organizational maintenance level. The design shall facilitate the removal and replacement of
failed light elements, control units or power source, as applicable, at the organizational
maintenance level. No repair of failed light elements, control units, power source, connectors, or
mounting hardware shall be authorized. Power source charging shall be accomplished at the
intermediate maintenance level.
3.8.3 Support equipment. Removal and replacement of light elements, control units, or
power source at the organizational level shall be performed using common hand tools. Support
equipment at the organizational level shall consist of a portable tester which shall verify the
operation of either one, or up to nine, installed lighting assemblies in an aircraft without
operation of the engines or auxiliary power unit. A charger, used at the intermediate level, shall
have charge rates such that the power shall be fully charged in less than ten hours. Design and
construction of peculiar support equipment shall comply with MIL-PRF-28800.
3.9 Safety. The lighting subassembly safety sub-program of the systems effectiveness
program shall be developed and conducted in accordance with MIL-STD-882. The design of the
EELS shall be in accordance with the hazard and safety requirements of MIL-STD-1472.
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