Kazan Helicopters Mi-17-1V Flight Manual page 65

M,,·17·1 B. Flight manual
(12) To perform simultaneous run up of the engines including a power rating
at which the helicopter liftoff is excluded proceed as follows:
(a) iviake sure that the engines and main gearbox are warmed up. Test
the EEC - free turbine circuits proceeding as instructed in (7).
(b) Set the throttle control twist grip to the rightmost position.
(c) Operate the main rotor speed trim selector switch on the collective
pitch control lever to set a main rotor speed of 95%
(d) Pull the collective pitch control lever up to a position at which power
is increased to a level excluding the helicopter liftoff. Make sure that
the collective pitch control levers move smoothly and collective
pitch control lever hydraulic unlocking clutch operates normally.
(e) Make sure that pulling up of the collective pitch control lever causes
the engine power increase.
(f) Push the collective pitch control lever fully down. Make sure the en-
gines run at steady power, note the engines speeds at this power
setting and turn the throttle control twist grip to the leftmost position
corresponding to idling. Run the engines at this power for 1 min.
(g) Check the power plant operational characteristics which should be
in compliance with the data indicated in Table 2.9.
The schedule of engines simultaneous ground testing is shown in
Fig.3.5
(13) Perform independent run up of the engines with setting the take-off
power at direct headwind or at headwind blowing at an angle of 20° to
the right.
Before carrying the independent run up of the engines with setting of the
takeoff power, load the helicopter to a gross weight not less than 13000
kg.
Perform independent run up of the engine with setting the take-off power,
proceeding in accordance with the Engine Maintenance Manual.
(14) In the course of the engine ground test check the II1P-117M EPR indicator
for correct readings as follows:
(a) Set the normal power corresponding to a gas generator rotor speed
0.5% above the values derived from graph "C" in the engine Log
Book for an actual ambient temperature.
(b) Make sure that the side index of the EPR indicator of the engine be-
ing tested is at the upper half of central index "H".
Notes: 1. The normal power gas generator rotor speed is derived from the
Engine Log Book by the Flight Engineer.
2.lf the side index is beyond the established limits at the power
setting being checked adjust the EPRindicator.
Set and rrlonitor the engine power ratings using the Ii1P-117M
EPR indicator readings, the gas generator rotor speed and TGT
maximum limits established for the selected power should not
be exceeded.
In case of failure of the EPR indicator, set and monitor the engine power
ratings basing on the gas generator rotor speed.
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