SYSTEMS DESCRIPTION
Cabin cooling is provided by a 12,000 Btu, 30-cfm, refrigera-
tive type air conditioning system. The principal compo-
nents of the air conditioning system are the compressor
and clutch unit (belt-driven from a drive pulley on the en-
gine), the retractable condenser on the center line of the
fuselage bottom skin, the dehydrator beneath the right
front seat, the evaporator module beneath the left front
seat, the air conditioner condenser-extended warning light
on the lower edge of the floating panel, the various retract-
able condenser limit switches, the system controls on the
control console, and the circuit breaker. The circuit breaker I
is located on the control console in airplanes with the
14-volt system and on the right subpanel on airplanes with
the 28-volt system.
The three-position retractable condenser is operated by an
electric motor and jackscrew actuator, and controlled by
two internal stops in the motor, two limit switches on the
condenser, the landing gear safety switch, and a throttle
limit switch. The three retractable condenser positions are
ground extension, flight extension, and retracted.
When the airplane is on the ground and the air conditioner
is turned on, the condenser extends to the ground exten-
sion (lowest) position below the fuselage bottom to facili-
tate condenser cooling by ambient air from the propeller
slipstream. More effective cooling on the ground can be
accomplished by maintaining a propeller setting of at least
1200 rpm with the airplane nosed into the wind. With the
condenser in the ground extension position, the air con-
ditioner condenser-extended warning light on the lower
edge of the floating panel is illuminated.
When the airplane is in flight with the landing gear retracted
and the air conditioner is turned on, the condenser extends
only to the flight extension position. The flight extension
position produces less drag than the ground extension
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FAA Approved
Revised: November, 19n
P/N 35-590118-35
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