Tb3-117Bm Engines Starting - Kazan Helicopters Mi-17-1V Flight Manual

M,,·17·1B. Flight manual
8. The APU continuous operation time in the "STBY GEN"
(PE3EPBbl. rEHEPAT) mode should not exceed 30 min,
and thereafter the API) should be shut down fOr 15 min. for
the purpose of cooling.
9. In case of necessity it is allowed to perform five successive
air bleed cycles for starting the TB3-117BM engines, each
cycle having a duration not exceeding 45 s with intervals be-
tween the cycles of not less than 1 min. during which the
APU is run at idle. In this case, the total time of continuous
operation should not exceed 13 min., and thereafter the
APU should be shut down and cooled for not less than 15
min.
10. Never bleed air for starting the TB3-117BM engine nor se-
lect the generator mode for the starter-generator while the
APU is starting.
3.6. TB3-117BM engines starting
(1) The Captain or, upon his order, the Flight Engineer are authorized to start
or shut down the engines. In this case the Captain should be seated at
his station. Only the Pilot is authorized to warm up and run up the power-
plant.
(2) The engines starting order depends on the wind direction and dictated by
the even usage of the established service life of the engines as well. The
first to be started is the engine at the leeward side.
(3) Before start it is necessary to call OFF ROTORS and set the engine
mode selector switch to START (3AnYCK) and the LEFT RIGHT (nEB.
nPAB) selector switch as required. Make sure that the fuel fire shutoff
valves switches are set to OPEN (OTKPbITO).
(4) Having received reply ALL CLEAR depress the START (3AnYCK) button
for 2 to 3 seconds and thereafter move the fuel shutoff valve of the en-
gine being started to OPEN (OTKPbITO).
The engine should gain the idling speed within not more than 60 s. The AUTO
CONT ON (ABTOMAT. BKnfOlIEHA) and STARTER ON (CTAPTEP
PA60TAET) annunciators should illuminatein the course of start. After com-
pletion of the automatic starting cycle the annunciators should go out (the
AUTO CONT ON" (ABTOMAT. BKnfOlIEHA) "aririLJriciatoriri 30 s arid the
STARTER ON (CTAPTEP PA60TAET) annunciator at the moment the gas
generator rotor attains a speed of60 to 65%).
If in the course of the engines acceleration up to the idling speed and
spinning up of the rotor the blades centrifugal droop limiters hit the stops,
this event being accompanied by pounding, the Captain should slightly
move the control stick to a position at which this pounding discontinues.
(5) In the course of start the Flight Engineer should monitor:
(a) Ground (aircraft) power source voltage.
(b) Rate of oil pressure rise in the engine and main gearbox.
Note: At gas generator rotor speed exceeding 45% the engine oil
pressure should be not less than 1
kgf/cm
2
•
(c) Gas generator rotor speed.
(d) Rate of the turbine inlet temperature rise.
(e) Pressure in the hydraulic system.
(f)
Starting line air pressure.
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