is equipped with a 6-cylinder Lycoming IO-540-K1G5 engine and a Hartzell
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.
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.
brake system includes toebrakes on the left and the right side of
rudder padals and a hand brake located below the instruments panel.
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
A selector lever
mounted on the instrument panel electrically controls the wing flaps.
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
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
fuel pump is provided for use in case of failure of the engine driven
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.
electrical accessories include the starter, the electric fuel pump,
the stall warning horn, the ammeter, and the annuaciator panel.
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.
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.
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
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.
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