Kazan Helicopters Mi-17-1V Flight Manual page 157

MI1-17-1B. Flight manual
failure (switching off) of the EEC the maximum gas generator rotational speed
should not exceed 102,5%.
In-flight troubles in the engine automatic control system require various ac-
tions of the pilot, which depend on the indications of troubles.
(1) Indications
(a) Variation in the gas generators rotor speeds within more than 1 %.
(b) The power ratings of one of the engines fail to change when the col-
lective pitch control lever is being moved.
Upon detection of these indications the main rotor speed is main-
tained automatically at 95±2%.
(2) Pilot's actions
(a) Upon detection of one of the above indications abort the mission
and land on the nearest aerodrome.
(3) Indications
(a) A difference in the gas generators rotor speeds of the engines ex-
ceeding 2 %.
(b) Spontaneous increase in the main rotor speed (one or both of these
indications).
(4) Pilot's actions in hovering during takeoff or pre-landing glide
(a) Land if at least one of the above indications are detected.
(b) If the main rotor overspeeds up to 101 %, smoothly turn the throttle
control twist grip to the left and simultaneously pull up the collective
pitch control lever to set the main rotor speed to 95±2%, and main-
tain it at this level manually (by moving the collective pitch control
lever up and turning the throttle control twist grip to the left).
(5) Pilot's actions under other conditions of flight
(a) Pull up the collective pitch control lever to set the main rotor
speed to 92 to 93 %.
(b) Determine the nature of the automatic control system trouble,
for this purpose smoothly push down the collective pitch con-
trollever, preventing the main rotor speed increase up to 98
%, and then pull it up. The following cases of variations in the
gas generator rotor and main rotor speeds may take place:
1). Case 1. Operation of the collective pitch control lever
causes variation in the gas generator rotor speeds of both en-
gines, the main rotor speed Is maintained automatically within
the limits of 95±2%. In this case establish horizontal flight and
an airspeed of 100 to 150 km/h. Abort the mission and land on
either the departure or nearest aerodrome.
2). Case 2. With the collective pitch control lever being pushed
down the gas generator speed of one of the engines de-
creases, with the collective pitch control lever being pulled up
this speed increases, the main rotor speed is maintained
automatically within 95±2%, the other engine runs at takeoff
power and its gas generator speed does not change.
In this case smoothly push the collective pitch control lever
down to set the main rotor speed to 95 %. Smoothly move
down the throttle control lever of the engine with the faulty
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