Kazan Helicopters Mi-17-1V Flight Manual page 158

MH-17-1B. Flight manual
automatic control system to reduce its gas generator rotor
speed by 3 %. The gas generator rotor speed of the engine
with the serviceable automatic control system rises. Further
piloting of the hetlcopter does not differ from normal proce-
dures except for more smooth operation of the control stick
and the collective pitch control lever since keeping of the main
rotor speed within the range of 95±2% is ensured by the
automatic control system of only one engine (the throttle con-
trol twist grip should be set in this case to the rightmost posi-
tion). Abort the mission, establish a horizontal flight speed of
100 to 150 km/h, and execute vertical or running landing on
the nearest field or aerodrome, if flight is performed in the
aerodrome zone.
3). Case 3. With the collective pitch control lever being pushed
down the gas generator rotor speed of one engine (operating
at takeoff power) does not change, the gas generator rotor
speed of the other engine decreases slowly, and the main ro-
tor speed is not maintained at 95±2% but rises. In this case
stop pushing down the collective pitch control lever as soon as
the main rotor speed reaches 96 %. Turn the throttle control
twist grip to the left until a main rotor speed of 95% is attained.
To change the required power setting, control the engines by
smoothly turning the throttle control twist grip with simultane-
ous deflection of the collective pitch control lever so as the
main rotor speed is maintained at 95±2% manually (the collec-
tive pitch control lever up - the throttle control twist grip to the
right, the collective pitch control lever down - the throttle con-
trol twist grip to the left).
Abort the mission, establish a horizontal flight speed of
100
to
150
km/h and execute vertical or running landing on the near-
est selected field or aerodrome, if flight is performed in the
aerodrome zone.
(6) Failure of EEC free turbine controls. Indications
(a) Illumination of the FREE TURB OVERSP L ENG - R ENG
(nPEBbIUjEHVlE060POTOB CB060AHOVI TYP6V1Hbl JlEB. AB.
- nPAB. AB.) annunciator.
(b) The engine continues operating.
(7) Pilot's actions
(a) Momentarily switch off the EEC of the affected engine.
(b) Make sure the FREE TURB OVERSP L ENG - R ENG annunciator
has gone out.
(c) Switch on the engine electronic control (EEC). If the annunciator
continues illuminating after switching on of the EEC increase alert-
ness in monitoring the engine operational pararneters, abort the
mission and land on the aerodrome of departure.
(d) If after switching on of the EEC the annunciator is not illuminated
make sure that the engine monitoring instruments readings are
normal and continue performing the mission, increase alertness in
monitoring the engine operational parameters.
Warning: In all cases if after illumination of the FREE TURB
OVERSP L ENG" R ENG annunciator the deviation of
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