Climb - Kazan Helicopters Mi-17-1V Flight Manual

M,,·17·1B. Flight manual
the helicopter by reducing the collective pitch down to a level, at which
the helicopter stands firmly on the ground, push the control stick forward
and simultaneously increase the collective pitch to establish acceleration
up to a speed of 20 to 50 krn/h. increase the main rotor coiiective piton
further on (up to limited takeoff power) and slightly pull the control stick
back to lift off.
(3) After lift-off with shallow climbout accelerate to a speed of 120 km/h and
proceed to climb. The use of this procedure yields a takeoff distance of
250 to 300 m.
(4) At takeoff from fields of limited dimensions surrounded by obstacles climb
at a speed of 50 to 60 km/h to reduce the takeoff distance.
4.5. Climb
(1) The best climb speed is 120km
Ih
at altitudes up to 2000
rn,
100 km/h at
an altitude of 3000 m, 4000m, 5000 m; 90 km/h at an altitude of 6000
km/h. Climb is performed normally at engine maximum continuous power
rating, for rate of climb refer to Fig.1.1 Oa (section 1). In case of necessity
climb may be performed at takeoff power within values indicated in the
Table 2.9a (for not more than 15 min) and at power ratings below maxi-
mum continuous one.
(2) Engine power is set by the Pilot by referring to the II1P-117M (EPR) indi-
cator at an altitude up to 2500 m and is determined by setting of its side
index with respect to central bugs 'H' and 'K':
(a) Takeoff power - side indexes are above central bug "H".
(b) Maximum continuous power - side indexes are above central bug
"K"
up
to
alignment with index
"H".
(c) Cruisingpower-sideindexesare aligned with or below central bug
"K".
Notes: 1. Engine power is determined by the II1P-117M (EPR) indicator
until the gas generator rotor maximum limit speed or maxi-
mum TGT are attained (Ref. Table 2.8). Upon attainment of
the gas generator rotor maximum speed or maximum TGT
specified in Table 2.8, set and monitor the power referring to
the parameter first to attain its maximum limit.
(3) In climb at maximum continuous power and the main rotor pitch constant
the main rotor speed is maintained constant at 95±2% up to altitude of
3600 m, ISA. In further climb the main rotor speed decreases due to re-
duction of the engines output power by the gas generator rotor speed
governors. In this case smoothly reduce the main rotor pitch to avoid a
main rotor speed drop below 92% (94-95% at altitude close to the service
ceiling).
Under ISA conditions the engines maximum continuous power is limited
from altitude of 3600 m. If the outside air temperature is below the ISA
schedule, limitation of power will take place at a higher altitude and vice
versa.
In climb at cruising power the main rotor speed is maintained constant up
to altitude of 3600m.
In climb at takeoff power and a constant main rotor pitch the main rotor
speed is not maintained automatically constant at a level of 92 to 94%.
In this case maintain the main rotor speed by successive reduction of the
collective pitch.
4-8