provided to (a) prevent temporary upset and permanent damage to the avionics
suite, (b) prevent structural damage to the airframe and (c) prevent lightning
ignition of fuel tanks and systems.
30.8 Precipitation static. The contractor shall provide E design
criteria to ensure that the system shall be designed to prevent P-static charges
from degrading system effectiveness. Precipitation static control measures
shall be included only where analysis or tests show that such measures are
required and resistivity shall be that necessary to eliminate unacceptable
responses. Static discharges shall be used only if analysis or tests show they
30.9 HERO. The system design shall include provisions to protect ordnance
subsystems from inadvertent ignition or dudding caused by any form of electro-
magnetic or electrostatic energy. All wiring, cabling and hardware associated
with the ordnance subsystems shall be carefully designed to prevent stray pickup
and eliminate undesired energy. All modes of operation during the mission,
including loading, unloading, checkout, and prelaunch shall be considered.
30.10 RADHAZ. The system design criteria shall include provisions for
protection of personnel from RF, electromagnetic, electrostatic and shock
hazards in accordance with Requirement 1 of MIL-STD-454. Where possible,
protection provisions shall be designed into associated subsystems/equipments.
When protection by design is not technically feasible, adequate safety pre-
cautions shall be included in operating and maintenance manuals.
30.11 Operational EKE. The system design shall provide compatibility with
the external electromagnetic environment (EKE). Consideration shall be given to
the intended mission profiles, the available electromagnetic environment data
and the degree to which the external environment can reduce the desired
effectiveness of the system. The aircraft and its subsystems shall meet all
design requirements when immersed in a friendly (carrier deck) or hostile
external electromagnetic environment. Mission and safety requirements shall be
met during operations when electromagnetic energy originating from friend or foe
is coupled to the aircraft through CFE, GFE, GSE and external electrical power.
Electromagnetic-environmental data is available from MIL-HDBK-235 and
30.12 Emission control. The system design shall include an emission
control function which prevents electromagnetic radiation from the system in
excess of -110 dBm/M at 1 nautical mile.