MIL-PRF-85676A(AS)
device from the ARMED and from the ON positions. When either the cockpit control or the
control at the cabin attendant's seat is ON the lights shall remain lighted upon interruption of the
aircraft's normal electrical power source, except as noted in 3.4.2. When the cockpit control is in
the ARMED position, the lights shall illuminate upon interruption of the aircraft's normal
electrical power sources and remain illuminated except as noted in 3.4.2. Operation of the
emergency lighting system shall not be dependent upon formal aircraft power.
3.6.1.2.2 Cabin control device. The cabin control device shall provide a means to
safeguard against inadvertent operation and turn on the emergency light system, even with the
cockpit control device in the OFF or ARMED position.
3.6.1.3 Aircraft configured to carry only passengers. The control unit used in the EEL
on aircraft configured to carry only passengers shall conform to 3.6.1 and 3.6.1.1 through
3.6.1.2.2.
3.6.2 Power source. The integral power source in the control unit shall provide power
for operation of the complete lighting subassembly. The energy supplied to each emergency
lighting unit shall provide the required level of illumination for not less than 10 minutes at the
critical ambient conditions after emergency landing (see 6.12.1). Subsequent to satisfactory
preflight check and a 1-hour mission during which the power source is charged, the power source
shall remain installed without receiving a charge for a period of one week and still provide
sufficient power to enable the lighting subassembly to meet the performance requirements stated
herein.
3.6.2.1 Shelf life. The power source shall have a minimum shelf life of two years and a
minimum service life of two years. Non-emergency operation of the subassembly during its
service life shall be limited to the performance of go/no-go power source checks (see 6.11).
3.6.2.2 Rechargeable power sources. If rechargeable power sources are used as the
energy supply for the emergency lighting system, recharging of the power sources from the
aircraft's main electric power system is permitted in accordance with MIL-STD-704 provided
that the charging circuit is designed to preclude inadvertent power source discharge into charging
circuit faults. It is desirable that the charging system for the emergency lighting system shall
recharge within 1-hour to facilitate aircraft dispatch. However, achievement of this charging rate
shall not reduce the system integrity.
3.6.3 Means of activation. The system shall be activated when any of the following
events occur: The loss of power, aircraft immersion in water, aircraft inversion or crash. Aircraft
operations such as take off and landing, taxi, maintenance or post flight power down, including
application of external auxiliary power, shall not activate the EELS.
3.6.3.1 Rotary wing and tilt rotor aircraft. The lighting subassembly shall automatically
activate when there is either a loss of power, aircraft immersion in water, aircraft inversion or
crash.
3.6.3.2 Fixed wing and lighter-than-air aircraft. When the cockpit control is in the
ARMED position, the lights shall illuminate upon interruption of the aircraft's main electrical
power system and remain illuminated except as noted in 3.4.2.
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