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Air Supply / Air Conditioning

Air Supply / Air Conditioning. S64F Model Helicopter. General Description.

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Air Supply / Air Conditioning

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  1. Air Supply / Air Conditioning S64F Model Helicopter 9-

  2. General Description The Environmental Control System (ECS) consists of a cooling turbine, pre-cooler, a combined primary heat exchanger and water condenser, an electronic temperature control/sensor, a temperature control valve, a jet-pump assembly, and two turbine inlet valves. The Environmental Control Unit (ECU) itself is located behind the cockpit in the “attic” and can be utilized in either a heating or cooling mode of operation as desired by the pilot. 9-

  3. General Description The ECS control panel is located at the aft portion of the overhead panel and consist of a two-position ON/OFF switch, a two-position HI/LOW switch, and a temperature selector rheostat. The ECS can be operated in either the NORMAL mode (HI) or ECONOMY MODE (LOW) and the control/sensor allows the pilot to select the desired temperature by rotating the temperature selector rheostat to the desired position (counter-clockwise for cooler temperatures and clockwise for warmer temperatures). 9-

  4. General Description The system also incorporates a Low Limit / High Limit Temperature Control Protection system that prevents either freezing or overheating that could result in damage to the nonmetallic distribution ducting that is located downstream of the ECU. Since reheater / condenser circulation air is at approximately the same temperature as the cockpit air supply, the 35 ± 3°F (1.67± -.16° C) control low limit setting of the control effectively prevents freezing conditions from existing in the distribution ducting. Conversely, a high limit circuit limits supply air temperature delivered from the unit to 180 ± 15°F (82.2 ± -9.4° C). 9-

  5. Pre-Taxi Check NOTE: First flight of the day; check ECS Fire shutoff circuit: 1. ECS – Power On RESULT: Air flow felt in cabin 2. Rotary switch (fire warning test panel) – Position 1. Both fire warning lights on the instrument panel and both fire warning lights on the engine quadrant should illuminate. 3. ECS Airflow CEASES 4. Press fire warning lights in instrument panel to reset. 5. ECS Airflow RESTORED 6. Rotary switch – NORM 7. All fire warning lights - EXTINGUISHED 9-

  6. Operation Operation of the ECS consists of turning the system to the ON position, thus energizing the 28-volt power supply, select either HI or LOW and then select the desired conditioned air temperature with the temperature selector rheostat. The system can be operated in either the Heating or Cooling Mode of operation as described below: 9-

  7. Heating Mode If the pilot selects a high temperature it does not matter which mode of operation (NORMAL or ECONOMY) has been selected because selection of a high temperature supply will automatically switch to the ECONOMY mode (low turbine flow). 9-

  8. Cooling Mode For operation in the cooling mode, select ECONOMY mode (or LOW switch position) and then select full cold with the temperature rheostat. Allow the temperature to stabilize a short time, and then select NORMAL mode (HI switch position) to obtain additional airflow. Modulate the temperature selector rheostat to provide the desired conditioned air temperature.  The pilot has the choice of selecting NORMAL or ECONOMY modes that operate in the following manner: 9-

  9. Normal Mode The primary turbine inlet valve senses actuator pressure of the temperature control valve and when maximum cooling is selected, this valve remains in the full open position; however, when warmer cabin air is selected, the economy valve begins to close prior to the temperature control valve opening, thus reducing cold air flow out of the turbine before adding hot air and reducing total bleed flow required for heating. When temperature selector rheostat is rotated to the maximum heat position, turbine flow is reduced by approximately 50%. 9-

  10. Economy Mode Control pressure air is provided to the actuator driving the valve to its minimum position and a check valve in the actuator air inlet line prevents feed back of actuator pressure to the temperature control valve resulting in the bleed air flow being reduce by approximately 50% in this mode. When the ECS is operated at low engine power settings, such as during prolonged ground operations when bleed air pressure is low, a secondary turbine inlet valve will automatically open to admit increased airflow through secondary nozzles, thus increasing cabin cooling and ventilation. When operating at higher engine power settings, the secondary turbine nozzles are closed due to the increased engine bleed pressure. 9-

  11. Circuit Breakers System Label Buss Amps Temperature Control ECU TEMP CONT No 2 28VDC Primary3ECU Control Panel ECU BLD AIR CONT No 1 28VDC Primary3Carbon Monoxide Detector ECU BLD AIR CONT*No 1 28VDC Primary3*NOTE: The Carbon Monoxide detector is connected to the same circuit breaker as the ECU control panel.SECTION I - OPERATING LIMITATIONS All limitations contained in Section 1 of the Flight Manual apply. 9-

  12. Normal Procedures BEFORE STARTING ENGINE • ECS Power Switch – OFF  SELF TEST OF CARBON MONOXIDE DETECTOR NOTE: When power is applied to the Model 452 CO Detector, a self-test routine begins. 1. Avionics Master Switch - ON 2. Observe Green Light on CO GUARDIAN CO Detector – Flashes Twice 3. Amber Light – Flashes Twice 4. Green Light – Steady ON 9-

  13. Normal Procedures NOTE: A failure of the CO sensor, temperature Sensor, or the Micro-controller will result in the following failure indications: The Amber LED will continue to flash at an approximately rate of 1 second on and 1 second off until the failure is cleared or power is removed from the unit. 9-

  14. Normal Procedures PRE-TAKEOFF ECS Power – As desired ECS HI/LOW Switch – As desired ECS temperature selector rheostat – As desired POWER ASSURANCE PROCEDURE ECS Power – OFF 9-

  15. Normal Procedures After Landing - Parking NOTE: Last flight of the day; check ECS Engine Fail shutoff circuit: 1. ECS Power - ON RESULT: Air flow felt in cabin 2. N1 lever – SHUTOFF ECS Airflow Ceases ECS Power - OFF 9-

  16. Emergency Procedures ECS Switch - OFF, if any one of the following occurs: Engine failure Engine over temperature Smoke or fumes in the cabin Insufficient power CO Detector Amber LED illuminates NOTE: In the event of an engine failure, the ECS becomes inoperative to allow the maximum performance of the remaining engine 9-

  17. PANEL WORDING FAULT CONDITION PILOT CORRECTIVE ACTION OUTLET DUCT TEMP (amber) Temperature in the cabin duct has exceeded 200°FECS – OFF. If light goes out, then reduce temperature selector rheostat setting and HI/LOW switch to LOW.ECS – As desiredCO DETECTOR ALARM • If the Amber Alarm LED illuminates, press the TEST/RESET button once. • If the alarm continues to operate by a flashing Amber (blink 4 times then off for 4 seconds) LED then: • ECS Power – OFF • Windows and Vents – OPEN • Don’t smoke • If Amber LED extinguishes, continue flight without ECS, otherwise land as soon as practicable. NOTE: A blinking Amber light on the unit will stay active until the Carbon Monoxide (CO) level goes below 50 Parts per million (PPM). • NOTE: DO NOT recycle the unit through the circuit breaker as there is a three minute delay for the CO sensor to stabilize at each startup. 9-

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