Descripción y operación de los componentes principales de los sistemas del helicóptero Bell 206

Instituto Tecnológico de Tijuana[pic 1][pic 2]

Carrera:

Ingeniería en Aeronáutica (IAE)

Asignatura:

Helicópteros

Descripción y operación de los componentes principales de los sistemas del helicóptero Bell 206

Nombre del maestro:

Francisco Cintora Cota

Alumnos:

Ayala Ramírez Luis Antonio        17212847

VOLUME 3 – EQUIPMENT

AIR DISTRIBUTION (VENTILATION)

Air for cabin ventilation is obtained by opening sliding windows in each of the entrance doors. Helicopters S/N 4 through 253 provide additional air for cabin ventilation by a ram air scoop mounted under the forward transmission fairing. Four adjustable valves, located in forward and aft cabin roof, provide air distribution for passenger and crew areas. Helicopters S/N 254 and subsequent provide ram air ventilation for the crew area only through ram air grilles located in nose of helicopter. This additional air is obtained by pulling VENT control knob under instrument panel. Positioning DEFOG BLOWER switch or circuit breaker on overhead panel to ON will circulate air onto windshield to defog.

• RAM AIR SYSTEM (Helicopters S/N 4 through 253).

In flight, ram air is forced into the ram air scoop and is distributed through ducts, located in the cabin roof, to the cabin through four adjustable valves in crew and passenger compartments.

• RAM AIR SYSTEM (Helicopters S/N 254 through 2488).

The ram air system is part of vent and defog system. With VENT control knob pulled out, ambient ram air will be forced through ram air grilles, located on helicopter nose, into air plenum assembly then into crew compartment through defog system.

• VENT CONTROL CABLE.

Vent control cables are mounted on brackets on lower instrument panel. VENT control knob will lock in all positions when pulled and will unlock by pressing release button in control knob.

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VOLUME 4 - FUEL/HYDRAULICS 

FUELSYSTEM

• FUEL SYSTEM (Helicopter S/N 4 through 3566). 

 The fuel system (figure 28-l) incorporates a single bladder type fuel cell located below and aft of the passenger seat (figure 28-l). Installed within the fuel cell are two electrically operated boost pumps, lower and upper tank indicating unit and sump drain valve. Boost pumps are interconnected and supply fuel through a single hose assembly to the fuel shutoff valve and from the shutoff valve to the engine mounted fuel filter and pump. Boost pumps incorporate pressure switches in discharge ports and drain plugs in the pump drain port. The fuel cell is filled from the right side and has a capacity of 76 U.S. gallons (287.66 liters usable).

Access to boost pumps, lower tank unit and drain valve is from the bottom of fuselage and access to upper indicating unit is gained from a cover plate located on deck aft of passenger seatback. Access to fuel shutoff valve and vent line is in the fuel compartment located on the right side of access panel above filler cap. Provisions are also made in fuel compartment for combustion heater fuel, fuel pressure instrument line, and fuel pump purge line.

• FUEL CELL (Helicopters S/N 4 through 3566).

Fuel cell is a bladder type unit installed in the fuselage cavity below and aft of passenger seat and laced to helicopter structure.

• FUEL SYSTEM (Helicopters S/N 3567 and subsequent).

The fuel system (figure 28-2) incorporates a single crash resistant bladder type fuel cell located below and aft of the passenger seat. Installed within the fuel cell are two electrically operated boost pumps, lower and upper tank indicating unit and electrically operated sump drain valve. Boost pumps are interconnected and supply fuel through a single hose assembly to the fuel shutoff valve, and from shutoff valve to the airframe mounted fuel filter. Boost pumps incorporate pressure switches in discharge ports and drain plugs in pump drain ports. The fuel cell is filled from the right side and has a capacity of 91 U.S. gallons (344.44 liters usable).

Access to boost pumps, lower tank unit and solenoid drain valve is from the bottom of fuselage and access to upper indicating unit is gained from a coverplate located on deck aft of passenger seatback. Access to fuel shutoff valve and vent is in fuel compartment located on the right side above filler cap. Provisions are made in the fuel compartment for a fuel purging line to be installed at tank vent fitting for maintenance purposes.

• FUEL CELL (Helicopters S/N 3567 and subsequent).

Fuel cell is a crash resistant bladder type fuel cell located below and aft of passenger seat structure. The fuel cell is held to structure by screws.

FUEL DISTRIBUTION.

Fuel distribution consists of all fuel cell mounted components which transfer fuel, and monitor fuel quantity, fuel flow, or fuel pressure.

• FUEL PUMP AND FILTER ASSEMBLY.

The engine fuel pump and filter assembly are integral units mounted on the aft end of engine. Fuel enters engine fuel system at inlet port of the pump and passes through filter before entering gear elements of pump. Filter draining is accomplished by a drain valve mounted on filter housing. Fuel filter is monitored by a pressure differential switch located on lower firewall and connected electrically to fuel filter caution light. Refer to Allison Engine Company Operation and Maintenance Manual (5W2 for C-l 8 engine or 1 10W2 for C-20 engine) for detailed maintenance instructions.

• FUEL BOOST PUMP.

Two electrically operated fuel boost pumps are located in the bottom of fuel cell. Pumps are interconnected and furnish fuel through one supply line. Pumps are equipped with check and thermal relief valve, pump drain port, seal drain port, intake screen, and pump operating pressure switch located in discharge port of

pump. Pumps are protected by circuit breakers located in overhead console. Fuel pump motor/impeller cartridge can be removed without removing fuel boost pump assembly. Refer to paragraph 28-22 for replacement of motor/impeller

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