SECTBON
Vll
MOONEY
AlRPeCBNE
AND
SYSTEMS BESCRlPTlON
MODEL M204
dividually controlled and mixed to desired temperatures. The side fresh-air
sysiern has adjustable outlets near pilot's and co-pilot's knees.
The cabin overhead ventilating system works independently of cabin
heating
and ventilating system. Fresh air enters an intake on the dorsal fin and is con-
troiled by individual outlets above each seat,
A
master air vent control regu-
iates flow of air through the individual overhead outlets. This control is lo-
cated above the pilots seat back on
the overhead panel.
--
!
he cabin hear c~r>tioi is rnarlted CABIN \-+EAT. i7ulling cabin heat control aft
supplies heat to cabin and defroster
system. The cabin vent control is
marked VENT. Pt.~lling vent control
aft
supplies fresh air
to
lower cabin and
defrost system. i-tot and cold air
may
be
nixed
by
adjusting both heat and
veil%
contro!~. These controls
rnay
be udj~isled between
full
open
and
full
cissod. The right side eirscoop has outlels under the side panel for installa-
tion
of radio cooling duets. Cabiii hear will
be
more eRective with cowl
flap
closed.
The
windshield defrost system takes air from
She
cabin air distribution system
and
distribues this over the wintbshieid interior sufface any time heat arrdlor
i-resi? air valves are opened. Ptalling defrost conrroi full aft decreases flow lo
cabin
and
forces maxirnurn air to flow through defrost ducts.
An
optional
defrost
Mower motor system
Is
available
lo
force more
air
over the windshield
if
desired.
PlTOl
PRESSURE
8
STAflC
SYSTEM
A
piiot tube, mounted on lower surface
of
the
ieFL
wing, picks up airspeed
in-
dicator ram air.
A
heated pitot prevents pitot tube icing when flying in mois-
ture-iaden air.
A
pieot system drain valve is iocaeed on forward bottom skin of
ieR
wing just outboard of wing fillet. Static ports on each side of tailcone
supply static air pressure for the altirneler, airspeed indicator, and vertical
speed indicator.
A
static systern drain valve is located on fuseiage bolrorn
skin below taiicone access
door.
An alternab static pressure source valve
is
installed
in
the flight panel just
left
of The pilots control coiurnn. Aiternate
static air is taken from the cockpit and will affect fiigint instrument readings.
Performance variation charts in
Section V depict the difference between
prirnary and alternate static indications.
STALL
WARNiNG
SYSTEM
The electrical stall warning system uses a vane- actuated switch, installed in
the
lefi wing leading edge, to energize stall warning horn located in the cabin.
The stail warning switch is adjusted to provide aural warning at
4
4
to
8.7
Knots before the actual stail is reached and will remain on until the aircraft
flight attitude is changed toward a am-stalled condition.
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