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Page Title:
Precautions for electrical ignition subsystems |
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|  MIL-S-18471G(AS)
a. Protect aircrewmembers from injury and equipment and
escape system components from damage resulting from
ballistic hose or fitting failure during operation.
b.
Protect the ballistic hoses and fittings from mechanical
damage during normal ejection seat use, ejection,
installation, removal, or stowage.
Ballistic hose bends (elbows) in excess of 45 shall not be used.
3.2.2.13.3 Precautions for electrical ignition subsystems. Electrical
ignition subsystems shall be protected from hazards of electromagnetic radiation
in accordance with MIL-STD-1385 and shall have independently shielded circuits
secured against vibration and protected against short circuits or grounds
resulting from chafing. The subsystem shall be protected forom the environmental
conditions specified in 3.1.9. Junctions shall be designed to eliminate current
leakage to or from other aircraft circuits and to minimize hazards of electro-
magnetic radiation. The ignition subsystem electrical power supply shall be
used solely to supply power to the ignition system and shall be adequate to
ensure ignition under all service environmental conditions specified in 3.1.9.
Verification of electrical ignition subsystem non-susceptiblity to hazards of
electromagnetic radiation shall be conducted in accordance with MIL-STD-1385.
3.2.2.13.4 Installation and routing of STS and components. The STS
components shall be selected, designed, routed, and mounted as required to
provide foolproofness, to withstand system operational loads, and to withstand
relative motion between STS components and other subsystem(s) interfaces
without degradation of the STS during operation. The STS component location,
routing, and shielding shall also be selected to provide:
a.
Protection against heat that is capable of damaging or
degrading components.
b.
Protection to prevent damage during normal use.
c.
Accessibility to maintenance personnel for periodic
replacement of age limited components.
d.
Assurance of maintenance personnel safety during removal
or installation operations.
3.2.2.14 Personnel location subsystems.
3.2.2.14.1 Personnel locator device(s). A method for automatically
activating personnel locator device(s) upon ejection of the ejection seat
shall be incorporated. Personnel locator device(s) to be used shall be
specified by the detail specification. The means for actuating the device(s)
shall be designed and located to permit using activities to arm or safety the
locator device actuation subsystem as necessary without requiring removal of
the survival container or the ejection seat assembly from the aircraft. Arming
or safetying the subsystem shall be a task readily accomplished in flight.
A visible indication shall be provided to indicate the status of the subsystem
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