UH-60Q 直升机技术手册 直升机操作手册 1(27)

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2.30.2 Fuel Boost Pump. The helicopter fuel system contains an electrically-operated submerged fuel boost pump in each fuel tank. When the pumps operate, they provide pressurized fuel to the engine fuel inlet port. Each boost pump is controlled by a switch on the FUEL BOOST PUMP CONTROL panel (Figure 2-7). The two-position switch for each pump, marked ON-OFF, activates the pump for continuous operation to maintain a head of fuel pressure at the engine fuel inlet port, regardless of engine boost pump discharge pressure. An advisory light near each control switch indicates pump pressure and operation. A check valve in each pump discharge line prevents fuel re-circulation during fuel boost operation, and prevents loss of engine fuel line prime. #1 or #2 FUEL PRESS caution legend going on is also an indicator to turn on boost pumps. Power to operate the boost pumps is provided from the No. 1 and No. 2 ac primary buses through circuit breakers marked NO. 1 and NO. 2 FUEL BOOST PUMP, respec-tively.
2.30.3 Refueling/Defueling. A pressure refueling and defueling system provides complete refueling and defueling of both tanks from one point on the left side of the helicop-ter (Figure 2-23). Closed circuit refueling uses the pressure refueling system and its components. No electrical power is required for the system during refueling or defueling. The tank full shutoff valve is .oat-operated. A dual high-level shutoff system acts as back up for each other. The two high-level .oat valves close, causing a back pressure to the fueling/defueling valve at the bottom of the tank, closing the refuel valve. The tank empty automatic shutoff system is a function of the low-level .oat valve opening to allow air to be drawn into the line, closing the defuel valve. A .ller neck between the fuselage contour and the fuel cell is a frangible (breakaway) connection. Gravity fueling is done through .ller neck on each side of the fuselage for the respective tanks. Gravity defueling capability is provided through the drains.
Change 4 2-29

Section V FLIGHT CONTROLS
2.31 FLIGHT CONTROL SYSTEMS.
NOTE

Flight near high power RF emitters such as microwave antennas or shipboard radar may cause uncommanded AFCS and/or stabilator control inputs. Electromagnetic interference (EMI) testing has shown that the master cau-tion light may illuminate before or simulta-neously with any uncommanded stabilator trailing edge movement, with 4° or 5° of movement being the maximum.
The primary .ight control system consists of the lateral control subsystem, the longitudinal control subsystem, the collective pitch control subsystem, and the directional con-trol subsystem. Control inputs are transferred from the cockpit to the rotor blades by mechanical linkages, and hydraulic servos. Pilot control is assisted by stability aug-mentation system (SAS), .ight path stabilization (FPS), boost servos, and pitch, roll and yaw trim. Dual cockpit controls consist of the cyclic stick, collective stick and ped-als. The pilot and copilot controls are routed separately to a combining linkage for each control axis. Outputs from the cockpit controls are carried by mechanical linkage through the pilot-assist servos to the mixing unit. The mixing unit combines, sums, and couples the cyclic, collective, and yaw inputs. It provides proportional output signals, through mechanical linkages, to the main and tail rotor controls.
2.31.1 Cyclic Stick. Lateral and longitudinal control of the helicopter is by movement of the cyclic sticks through push rods, bellcranks, and servos to the main rotor. Move-ment in any direction tilts the plane of the main rotor blades in the same direction, thereby causing the helicopter to go in that direction. Each cyclic stick grip (Figure 2-11) con-
tains a stick trim switch, marked STICK TRIM FWD, L, R and AFT, a go around switch, marked GA, trim release switch, marked TRIM REL, a panel light kill switch, marked PNL LTS, a cargo release switch, marked CARGO REL, and a transmitter ICS switch, marked RADIO and ICS. Refer to major systems for a complete description of switches on the cyclic grip.
　
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