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Defogging and defrosting system tests for pressurized aircraft |
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|  MIL-T-l86O6(Aer)
maximum speed (VmEX) can be obtained, accelerate the airplane at maximum rate to its
maximum velocity and record data to define the performance of the cooling system
during this transient condition, If it is practicable, maintain the airplane at
maximum power long enough to obtain stabilized temperature conditional or at least to
establish the trend of the cabin temperature rise.
4.2.2.10 If the airplane is equipped with two or more cabin pressurizing
sources, one pressure source shall be directed away from the cabin or operation
stopped in order to determine if design cabin differential pressure can be maintained
at the normal cruise altitude. Proper operation of the air conditioning and pressure
control system shall be demonstrated in this condition.
4.2.2.11 On aircraft equipped with combustion heaters, locate an atmos-
pheric temperature condition which will require intermittent or low output operation
of the heater(s) to satisfy cabin heat demands, Continue to fly the airplane under
this condition until stabilization of cabin temperature is obtained, Observe cabin
temperature to detect cyclic variation.
4,2,2,12 During flight at normal cruise altitude the performance of the
ventilation provisions for the galley and sanitation areas shall be tested as
specified In Section 3.2.2.
4.2.2.13 Heating and ventilating installations in rotary wing aircraft shall.
be satisfactorily demonstrated during all directions of flight and during hovering,
4,2,2 14 Heating and ventilating systems installed in airships shall be
demonstrated satisfactorily for all conditions of flight, including hovering and
tactical maneuvers.
4.3 Defogging and defrosting system tests for pressurized aircraft. -These
tests shall be made when the sea level dew point temperature is as near as practicable
to 85 degrees Fahrenheit, but no lower than 60 degrees Fahrenheit. The flights should
be made during early morning or late evening when the dry bulb temperature is low.
4.3.1 Test procedure. The airplane shall be climbed to the lowest altitude
at which a true atmospheric temperature of minus 65 degrees Fahrenheit exists. The
airplane shall loiter at this altitude, at the minimum engine power netting required
to maintain level flight, for a period of 30 minutes. A maximum rate of' descent dive
with the lowest practicable engine power setting shall be accomplished to the safe
minimum altitude, The airplane shall be descended through as much cloud as possible,
particularly at low altitude.
4.3.2 The above test shall be repeated with the dive being made at the
maximum allowable speed.
4.3.3 Tests shall be conducted with the system controls set for optimum
performance, however, the exact use made of the controls during the flights shall be
fully described.
4.3.4 The following test data shall be reported;
(a) See level dew point and dry bulb temperature during
test flights.
(b) Cabin temperatures at head and foot level taken at
regular intervals during the flight~ These tempera-
tures must also be recorded immediately before and
after descent.
(c) Defogging air temperature and temperatures at various
locations of the inner surface of the transparancies,
.
, (d)
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