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2.11.3 Fire Extinguishing Systems. A high-rate dis-charge extinguishing system provides a two-shot, main and reserve capability to either main engine compartment or APU compartment. Two containers are each .lled with liq-uid and charged with gaseous nitrogen. The containers are mounted above the upper deck, behind the right engine compartment (Figure 2-1). Both containers have dual out-
lets, each with its own .ring mechanism. Each extinguish-ing agent container has a pressure gage, easily viewed for pre.ight inspection. The system also has a thermal dis-charge safety port that will cause a visual indicator on the right side of the fuselage to rupture, indicating that one or both containers are empty. Electrical power to operate the No. 1 main and No. 2 reserve outlet valves is by the No. 2 dc primary bus through a circuit breaker, marked FIRE EXTGH. Power to operate the No. 2 main and No. 1 re-serve .re bottles outlet port valves and the directional con-trol valve is by the battery utility bus through a circuit breaker on the lower console marked FIRE EXTGH.
2.11.4 Fire Extinguisher Arming Levers (T-Handles). One APU T-handle is on the upper console (Figure 2-6) marked APU, and two engine .re extinguisher T-handles are on the engine control quadrant, marked #1 ENG EMER OFF and #2 ENG EMER OFF (Figures 2-6 and 2-10). The handle marked #1 ENG EMER OFF is for the No. 1 engine compartment, the handle marked #2 ENG EMER OFF is for the No. 2 engine compartment, and APU is for the auxiliary power unit compartment. When a handle is pulled, dc power actuates the .re extinguisher logic module to select the compartment to which the .re extinguisher agent is to be directed, and also energizes the circuit to the .re extinguisher switch. The ends of the handles house .re detector warning lights.
2.11.5 Fire Extinguisher Control Panel.

CAUTION
In case of .re when ac electrical power is not applied to the helicopter, the reserve .re extinguisher must be discharged. Fire extinguisher agent cannot be discharged into No. 2 engine compartment if ac elec-trical power is not applied to helicopter.
The switch, marked FIRE EXTGH, on the upper con-sole (Figure 2-6), has marked positions RESERVE-OFF-MAIN. The switch is operative only after one of the ENG EMER OFF or APU lever (T-handle) has been pulled. When the switch is placed to MAIN, after an ENG EMER OFF lever has been pulled, the contents of the main .re extinguisher bottle are discharged into the corresponding
Change 4 2-17

compartment. When the FIRE EXTGH switch is placed to RESERVE after an ENG EMER OFF lever has been pulled, the contents of the opposite .re extinguisher bottle are discharged into the selected compartment. The contents of the .re extinguisher bottle discharge into the compart-ment of the last lever pulled.
2.11.6 Crash-Actuated System. A crash-actuated sys-tem is part of the .re extinguisher system. An omnidirec-tional inertia switch is hard-mounted to the airframe to sense crash forces. Upon impact of a crash of 10 Gs or more, the switch will automatically .re both .re extinguish-ing containers into both engine compartments. Electrical power is supplied from the battery utility bus through a circuit breaker on the lower console, marked FIRE EX-TGH.
2.11.7 Hand-Operated Fire Extinguishers.

Exposure to high concentrations of extin-guishing agent or decomposition products
should be avoided. The liquid should not be allowed to contact the skin; it could cause frostbite or low temperature burns.

One hand-operated .re extinguisher (Figure 9-1) is mounted on the medical cabinet. A second .re extinguisher is on the copilot’s seat.
2.12 CRASH AXE.
One axe (Figure 9-1) is installed on medical cabinet.
2.13 FIRST AID KITS.
Three .rst aid kits (Figure 9-1) are installed, one on the back of the left pilot seat, one on the back of the right pilot seat, and one on the medical cabinet.
2-18 Change 4
Section III ENGINES AND RELATED SYSTEMS
　
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