Table of Contents
Advertisement
The copilot's instruments are connected to the right
pitot tube and the lower left and right static sources lo-
cated on the aft fuselage.
No alternate static source is
provided for the copilot's instruments.
ALCOHOL WINDSHIELD DEICE SYSTEM
The alcohol windshield deice system consists of an
alcohol tank, a pump, left and right-hand dispersal tubes,
and a switch breaker.
The alcohol tank, located in the aft end of the right
wing locker, has a 3.0 gallon capacity.
The tank should be
filled with isopropyl alcohol only.
Water dilution of the
alcohol is not recommended, as any water contained in the
alcohol will reduce the efficiency of ice removal and may
freeze on the windshield at very low temperatures.
The pump
located adjacent to the tank provides positive pressure to
the windshield dispersal tubes.
The left and right-hand
dispersal tubes located at the forward base of the windshield
provide flow pattern control throughout the aircraft's speed
envelope.
Each tube contains five holes which should be
inspected and cleaned with a small diameter wire as neces-
sary.
NORMAL PROCEDURES
Before Entering Aircraft
(1)
During the exterior inspection, check the wind-
shield dispersal tubes for cleanliness.
Check the
tank alcohol level.
Flow requirements are 3.0
gallons per hour of continuous operation.
During Engine Run up
7-12
(1)
Position the windshield deice switch breaker to ON.
Allow approximately 10 seconds for flow to begin.
Assure that each of the five holes in left and
right-hand dispersal tubes are flowing alcohol.
Return the windshield deice switch breaker to the
OFF position.
Advertisement
Table of Contents
