Piper Saratoga
                                                             PIPER SARATOGA-PA-32R-301
         This aircraft is equipped with a 6-cylinder Lycoming IO-540-K1G5 engine and a Hartzell HC-I3-YR-1RF propeller.

         The airplane is equipped with a retractable tricycle landing gear, which is hydraulically actuated by an electrically powered reversible pump. The landing gear is retracted or extended in about 7 seconds.
         EMERGENCY GEAR extension system allows the landing gear to free fall, with spring assist on the nose gear, into the extended position where mechanical locks engage.
       The nose gear is steerable to a 22.5 degree arc each side of the center through the use of the rudder paddals.

       The Oleo struts are of the air-oil type,  with  normal  extension  being 3.25 ± .25" for  the  nose    gear   and 4.5 ± .5" for the main gear under normal static load.

         The standard brake system includes toebrakes on the left and the right side of rudder padals and a hand brake located below the instruments panel.
         Dual flight controls are provided as standard equipment. A cable system provides actuation of the control surfaces when the flight controls are moved in their respective directions.
         The horizontal surface (stabilator) feature a trim tab/servo mounted on the trailing edge. This tab services the dual function of providing trim control and pitch control forces.
         The rudder is conventional design and incorporates a rudder trim. The trim mechanism is a spring-loaded recentering device.
         A selector lever mounted on the instrument panel electrically controls the wing flaps.

         The standard fuel capacity of the Saratoga II HP is 107 gallons, of which 102 gallons are usable. The inboard tank is attached to the wing structure with screws and nut plates and can be removed for service or inspection. The outboard tank consist of a bladder fuel cell that is interconnected with the inboard tank. A flush fuel cap is located in the outboard tank only.
          The fuel selector control has three positions, one position corresponding to each wing tank plus an OFF position.
          A fuel quantity indicator to measure the fuel not visible through the filler neck in each wing is installed in the inboard fuel tank. This gauge indicates usable fuel quantities from 5 gallons to 35 gallons in the ground attitude. The sole purpose of this gauge is to assist the pilot in determining fuel quantities of less than 35 gallons during the preflight inspection.
           An electric fuel pump is provided for use in case of failure of the engine driven pump.

           The 14-volt electrical system includes a 12-volt battery for starting and to back up alternator output. Electrical power is supplied by a 90-ampere alternator. The battery, a master switch relay, a voltage regulator and an over volatge relay are located beneath the floor of the forward baggage compartment.
           Standard electrical accessories include the starter, the electric fuel pump, the stall warning horn, the ammeter, and the annuaciator panel.
           The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly, and that the applicable system gauge should be checked and monitored to determine when or if any corrective action is required.
           Optional electrical accessories include the navigation lights, anticollision strobe lights, and instrument panel lighting and cabin courtesy lights.
            The ammeter in the alternator system displays in amperes the load placed on the alternator. It does not indicate battery discharge.

             The instrument panel is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments. The artificial horizon and directional gyro are vacuum operated and are located in the center of the left-hand instrument panel. The vacuum gauge is located on the upper left hand instrument panel. The turn indicator, on the left side, is electrically operated.
              The radios are located in the center section of the panel, and the circuit breakers are in the lower right corner of the panel. An optional radio MASTER switch is located on the lower center instrument panel in the switch cluster. It controls the power to all radios through the aircraft MASTER switch. The radio power switch has an OFF, and ON position.

               The system supplies both pitot and static pressure for the airspeed indicator, altimeter and vertical speed indicator. Pitot and static pressure are picked up by the pitot head on the bottom of the left wing. Al alternate static source is provided as standard equipment.

                The airplane has two separate baggage areas, each with a 100 pound capacity. A 7 cubic foot forward luggage compartment, located just aft of the fire wall, is accessible through a 16 22 inch door on the right side of the fuselage. A 17.3 cubic foot aft compartment is located behind the fifth and sixth seats and is accessible through the cargo door on the aft side of the fuselage and during flight from inside the cabin.
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