MOONEY
M20TN - MODEL TYPE-S
SECTION VII
AIRPLANE AND SYSTEM DESCRIPTION
7 -- 37
AIRPLANE FLIGHT MANUAL
ORIGINAL ISSUE -- 04-02-2008
3.
From this point on the heavy line, follow the trend of the curved lines, down to the horizontal
line representing cruise altitude. Then drop vertically down to the bottom of the chart and read
the duration in hours given on the scale.
4.
As an example of the above procedure (refer to Figure 7--12), 1400 PSI of pressure will safely
sustain the pilot and one passenger for 4 hours and 55 minutes at 28,000 ft.; however, cruis-
ing at 20,000 ft. would permit an oxygen duration of 7 hours and 55 minutes.
Light crew loads and relatively low altitudes will permit oxygen durations off the chart. Such dura-
tions can be calculated by determining the duration at 30,000 feet (by steps 1 and 2 above) and
multiplying by the “duration multiplier” shown on the right of the appropriate cruising altitude.
Example, Pilot only, at 1600 PSI has 11.25 hours duration at 30,000 ft. Duration Multiplier of 2.4
for 20,000 ft., gives 26 hours and 54 minutes duration. Oxygen durations off the chart obviously
exceed the airplanes duration. However, judicious choices of altitude for the number of persons
on board can permit flight planning for several fuel stops, without need for recharging oxygen
system at each stop.
--CAUTION--
Facial hair, beards and mustaches may prevent a proper seal between face and
mask, causing 16- 67% leakage. Duration chart may be invalid.
VACUUM SYSTEM
GX aircraft are all electric. There is no Vacuum System in the standard aircraft.
EMERGENCY LOCATOR TRANSMITTER
The Emergency Locator Transmitter (ELT) is located in the tailcone and is accessible from the
battery access door on the right side of the tailcone. The emergency locator transmitter meets
the requirements of FAR 91.52 and is automatically activated by a longitudinal force of 5 to 7 g’s.
The ELT transmits a distress signal on both 121.5 MHz and 243.0 MHz for a period of from 48
hours in low temperature areas and up to 100 hours in high temperature areas. The unit operates
on a self--contained battery. The battery should be checked at each annual inspection. The bat-
tery has a useful life of four years. However, to comply with FAA regulations it must be replaced
after two years of shelf life. The battery should also be replaced if the transmitter has been used
in an emergency situation or if accumulated test time exceeds one hour. The battery replace-
ment date is marked on the transmitter label.
On the unit itself is a three position selector switch placarded “ARM“, “OFF”, “ON”. The “ARM”
position is provided to set the unit to the automatic position so that it will transmit only after impact
and will continue to transmit until battery is drained to depletion or until the switch is manually
moved to “OFF”. “ARM” position is selected when the transmitter is installed at the factory and
switch should remain in that position whenever unit is installed in the airplane. The “ON” position
is provided so unit can be used as a portable transmitter or in the event the automatic feature was
not triggered by impact or to periodically test the function of the transmitter. Select the “OFF”
position when changing battery, when rearming the unit if it has been activated for any reason, or
to discontinue transmission.
NOTE:
If the switch has been placed in the “ON” position for any reason, the “OFF”
position has to be selected before selecting “ARM”. If “ARM” is selected directly
from the “ON” position the unit will continue to transmit in the “ARM” position.
