Cessna Grand Caravan 208B G1000 Manual page 210

SECTION 4
NORMAL PROCEDURES
ENROUTE CLIMB
At lower altitudes and cool outside air temperatures (below
approximately 10,000 feet), the engine will reach the torque limit before
reaching the ITT or N
maintained by POWER Lever advancement, the ITT and N
increase until an altitude is reached where ITT or N
POWER Lever positioning. When operating near the ITT limit, advance
POWER Lever slowly to allow the current ITT to be indicated. The rate
of power (and temperature) increase of the engine is greater than the
response rate of the ITT indicating system; therefore, a rapid POWER
Lever advance could allow an over-temperature condition to exist
momentarily in the engine before the over-temperature would be
indicated.
For maximum performance climb, the best rate-of-climb airspeed
should be used with 1900 RPM and maximum climb power. This speed
is 104 KIAS from sea level to 10,000 feet, decreasing to 87 KIAS at
20,000 feet.
For improved visibility over the nose, a cruise climb airspeed of 115 -
125 KIAS may be desirable at altitudes up to approximately 12,000
feet. Adjust the POWER Lever (in accord with the Maximum Engine
Torque for Climb chart in Section 5) with the PROP PRM set at 1900 to
prevent exceeding the maximum allowable shaft horsepower for the
ambient conditions. After Climb Torque is set, PROP RPM can be
reduced in accord the following table for improved passenger comfort.
Under no circumstances should the following limitations be exceeded:
1. The MAX TORQUE for the corresponding PROP RPM
2. A maximum climb ITT of 765°C
3. A maximum N
1900
1800
1700
1600
•
Engine operations which exceed 740° C ITT can reduce
engine life.
•
To achieve maximum flat-rated horsepower, use a
minimum of 1800 RPM.
If an obstruction dictates the use of a steep climb angle, climb with
Flaps UP and maximum continuous power at 86 KIAS.
4-46
(Continued)
limit. As the climb progresses and the torque is
g
of 101.6%
g
RPM
NOTE
U.S.
CESSNA
MODEL 208B G1000
will dictate
g
MAX TORQUE
1865
1970
1970
1970
FAA APPROVED
208BPHBUS-00
will
g