Steamly S2-S/Systems

SECTION 2. SYSTEMS

1 Helicopter

1.1 General

The Shergood Steamly S2-S is a single-engine steam-turbine powered helicopter. It employs a closed-loop steam system consisting of a boiler, a steam turbine, a condenser and a water reservoir. A fuel oil burner in the boiler provides the heat to produce steam which is then directed into the turbine through the throttle valve. Steam exiting the turbine is passed through a condenser with twin engine powered cooling fans.

1.2 Gross Weight

The maximum gross weight is 2,100 pounds.

1.3 Main Instrument Panel

Figure 1: Main instrument panel

1. Tail-Number plate	2. Low Fuel Warning Light	3. Fuel Indicator	4. HOBBS Time
5. Compass Card	6. Clock	7. Low Boiler Pressure Warning Light	8. Low RPM Warning Light
9. Boiler Pressure Differential Indicator	10. Turbine Pressure Indicator	11. Engine/Rotor RPM Indicator	12. Attitude Indicator
13. Vertical Speed Indicator	14. Altimeter	15.Airspeed Indicator	16. Turn and Bank Indicator

1.4 Mid Instrument Panel

1. Boiler Temp./Water Level/Fuel Pressure Indicators 2. Boiler Pressure Indicator 3. Amps/Volts Indicator 4. Fuel Flow Control 5. Intercom (RP only) 6. Deathray Main Power 7. Radio 8. Transponder 9. Governor

Figure 2: Mid instrument panel

1.5 Switch Panel

Figure 3: Switch panel

A switch panel is located at the bottom of the instrument panel and contains the majority of the switches and breakers in the aircraft. Left to right the switches are:

• Ignitor - Key switch that turns on the ignitors for the burner. Requires that electrical power be active as well.
• Batt. (Master) - Main electrical power from the battery.
• Dynamo (Master) - Main electrical power from the dynamo. The dynamo is powered when the engine RPM is at least 50%.
• Aux Fuel Pump - Provides fuel pressure to the burner via an electrically driven pump
• Feed Pump - Pumps water from the reservoir to the boiler.
• Inst. Lights - Provides light for the cabin from two lights mounted on the back wall.
• Nav. Lights - Powers the three navigation lights, right on the left, blue-green on the right and white on the tail.

1.6 Magnetic Compass

Figure 4: Magnetic Compass	Figure 5: Beacon
Figure 6: Fuel Cutoff	Figure 7: Rotor Brake

A magnetic compass (Figure 4) is mounted on top of the main instrument panel. Note that the magnetic compass is only accurate in straight and level flight and is subject to the following types of error:

• Oscillation - Turbulence and motion of the aircraft will cause the compass reading to oscillate. The more steady the aircraft is held in a level attitude, the more accurate the reading will be.
• Deviation - Magnetic fields generated by the aircraft itself can affect the compass reading. A compass card (Figure 1 (#5)) on the main panel provides corrections from indicated headings to actual headings.
• Turning Error - Magnetic dip causes the compass to produce erroneous readings while in a turn on certain headings. These errors are most pronounced near North and South headings. While close to a North heading, the compass heading shown will tend to undershoot the actual heading, and while close to a South heading the heading shown will tend to overshoot the actual heading. When on an East or West heading, this error will be negligible. You can use the acronym UNOS (Undershoot North, Overshoot South) to remember direction of the error.

1.7 Beacon

A flashing beacon is mounted on the belly of the aircraft. The beacon is activated through a switch (Figure 5) mounted under the pilot seat.

1.8 Fuel Cutoff

A red fuel cut-off lever (Figure 6) is mounted under the pilot seat. Fuel flow to the burner is on when the lever is in the horizontal position.

1.9 Rotor Brake

A rotor brake lever (Figure 7) is mounted under the pilot seat. The rotor brake is on when the lever is in the up position.

2 Rotor and Power Train System

The rotor configuration of this helicopter consists of a single main lifting rotor system and an anti-torque tail rotor system. Both systems are driven by the engine through the transmission system and are controlled by the flight control system.

2.1 Main Rotor System

The main rotor system consists of the main rotor hub and three main rotor blades. Each should be inspected separately during the pre-flight inspection. The main rotor is controlled through a swash plate and control linkages connected to the collective and cyclic controls in the cockpit.

2.2 Tail Rotor System

The tail rotor is mounted on the right side of the vertical stabilizer. It acts to counteract torque from the main rotor and provide yaw control of the aircraft in a hover, and coordination for turns at cruise speed. The tail rotor is controlled through anti-torque pedals in the cockpit that alter the pitch of the blades thus increasing or decreasing the tail-rotor thrust.

2.3 Main Transmission

Figure 8: Main Transmission

1) Primary Drive Shaft, 2) Bevel Gear, 3) Centrifugal Clutch, 4) Sprag Clutch, 5) Tail Rotor Drive Shaft, 6) Main Rotor Reduction Gear

The main transmission (Figure 8) translates power from the engine to the rotor system. Rotational power is supplied through the main drive shaft (#1) from the steam turbine. A bevel gear (#2) translates the horizontal rotation from the main drive shaft to a vertical input shaft to the transmission. The transmission includes a centrifugal clutch (#3) and a sprag clutch (#4), an additional bevel tap gear (#5) for the tail rotor drive shaft, and finally a reduction gear (#6) to reduce the RPM from engine to the RPM for the main rotor.