Main Surface Control Systems

The main surfaces (ailerons, rudder, and elevators) are controlled by mechanical control systems consisting of cables, pushrods, bellcranks, and torque tubes. Hydraulically-driven booster units provide most of the force required to move the surfaces. The booster units are driven by hydraulic pressure supplied simultaneously by the booster and utility hydraulic systems (seeFigure 2-46), each of which serves to power one portion of the booster units. System operation is such that failure or malfunction of any component of either system in any booster unit will allow normal function of the other system powering the same unit. A loss of hydraulic pressure in either hydraulic system results in a corresponding loss in the booster unit, and a proportionate loss of power to operate the unit. The aircraft may be controlled with complete loss of booster unit power by the use of trim tabs and engine power, plus coordinated, increased efforts of the pilot and copilot. Solenoid-operated shutoff valves in each surface control system can be actuated by switches on the control boost switch panel (seeFigure 2-46) at the flight station to shut off supply pressure to either of the systems. The valves are spring loaded and will open when deenergized (control boost switches in the ON position). A booster-off warning light for each switch is also powered by the solenoid shutoff valve switch and will illuminate when the switch is in the OFF position. An autopilot servomotor is cable-rigged to each booster unit to substitute for manual control during autopilot operation. Electrical power for operation of the booster shutoff valves is supplied from the essential dc bus through the AILERON, ELEVATOR, and RUDDER SHUTOFF VALVES circuit breakers on the copilot lower circuit breaker panel.

2.9.1.1 Rudder Booster Assembly

The rudder booster assembly is a single tandem-type hydraulic actuating cylinder that furnishes most of the force to actuate the rudder. During normal operation, fluid supplied at approximately 3,000 psi pressure is routed by solenoid-controlled, normally deenergized diverter valves through pressure reducer valves in each of the systems and from there, at a pressure of approximately 1,300 psi, to the rudder booster assembly. This system pressure produces desirable characteristics of sensitivity and surface travel for normal in-flight operation. Movement of the flap lever from the retracted (UP) position to approximately the 15-percent position or beyond will energize the solenoids of the diverter valves, actuating the valves in such a manner that the pressure reducers are bypassed, thereby permitting supply fluid at approximately 3,000 psi pressure to reach the booster assembly. This doubles the available actuating force and gives desirable characteristics of sensitivity and surface travel at low airspeeds such as are encountered in takeoff, landing, and flying traffic patterns, where flaps are used. The diverter valves are powered from the essential dc bus through the RUDDER HIGH BOOST CONTROL circuit breaker located on the copilot lower circuit breaker panel. The amount of pressure actuating the rudder booster assembly (both the booster and utility portion of the system) is indicated on pressure gauges located on the hydraulic panel (seeFigure 2-45) of the copilot instrument panel. Transmitters for these indicators are located downstream of the diverter valve, and, therefore, will show high-or low-pressure operation.

2.9.1.2 Aileron Booster Assembly

The aileron booster assembly is a single tandem-type hydraulic actuating cylinder that furnishes most of the force to actuate the ailerons. The booster assembly is furnished fluid through a pressure reducer at approximately 2,050 psi from both the booster and utility hydraulic systems.

2.9.1.3 Elevator Booster Assembly

The elevator booster assembly has dual actuating cylinders connected to the booster assembly output power lever that operates the elevator control surfaces. The actuating cylinders operate simultaneously by 3,000 psi pressure supplied by the booster and utility hydraulic systems, each of which powers one actuating cylinder.

Figure 2-46. Surface Control System

2.9.1.4 Main Surface Control System Controls and Indicators 2.9.1.4.1 Control Columns and Wheels

Control columns and wheels (seeFigure 2-47) installed at the pilot and copilot stations to operate the aileron and elevator surface controls are of the conventional type. Mechanical linkage actuates the hydraulically-powered booster unit control valves and servomotors for each of these surface controls. Pushrods (elevator) and a chain-and-cable arrangement (ailerons) connect the control column to bellcranks on torque tubes that are mounted under the flight station beneath the pilot and copilot seats. From there, dual sets of steel cables continue the elevator linkage as far as the pressure bulkhead at the extreme rear of the cargo compartment and the aileron linkage to the rear face of the center-section wing rear-beam web. From these points, pushrods and bellcranks pick up the motion and transmit it to the booster unit control valves and servo units.

2.9.1.4.2 Rudder Pedals and Adjustment Controls

Rudder pedals are of the conventional type. Each pair of rudder pedals can be adjusted individually by unlocking the rudder pedal adjustment control (seeFigure 2-48) and pushing or releasing the spring-loaded pedals to the desired position. The rudder pedals are used to operate the rudder boosters when hydraulic power is available and to operate the rudder manually when hydraulic power is not available. The pressure on the rudder pedals actuates the brake during either normal or emergency braking.

Figure 2-47. Control Wheels

2.9.1.4.3 Control Boost Switches and Warning Lights

The control booster unit shutoff-valve-actuating switches are located on the control boost switch panel (seeFigure 2-49) on the overhead control panel. There are six guarded, two-position toggle switches (ON with cover down, deenergized) that will actuate the shutoff valves to isolate the corresponding booster package and to energize six hooded warning lights that illuminate BOOSTER OFF when their respective switches are placed in the OFF position.

The panel switches supply power to the warning lights directly through the copilot lower circuit breaker panel when in the OFF position, and, therefore, furnish no independent indication directly of boost unit failure or that the shutoff valves are closed. The warning light only indicates that the switch is in the OFF position and dc power is routed to the solenoid shutoff valve. Individual pressure control from both the booster and utility systems is available to each boost package. The 28-Vdc power for the lights and valves is supplied from the essential dc bus through the SHUTOFF VALVES circuit breakers on the copilot lower circuit breaker panel.