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about 2 quarts usable, the corresponding ENG OIL LOW
caution capsule will illuminate.
Figure 2-3-3. Emergency Power Panel 712
2-3-14. Engine Start System. 712
The engine start system includes the hydraulic starters
on each engine, the engine start valves and the solenoidoperated
pilot valves on the utility system pressure control
modules, the START switch, and the start fuel solenoids
and ignition exciters on the engines.
When the start switch is moved to MTR, the respective
engine STARTER ON indicator light illuminates and the
start valve opens (fig. 2-3-4). The start valve applies
utility system pressure from the APU to the engine starter:
rotating the engine starter and compressor. At 15
percent N1, the ENG COND lever is moved to GND. The
start switch is immediately moved to START, energizing
the ignition exciter. Start fuel is sprayed into the combustor
and combustion begins. Before PTIT reaches 200
C,
the START switch is manually released to MTR. At MTR,
the start fuel valve is closed and the ignition exciter is
deenergized.
The engine then accelerates to ground idle speed. At 50
percent N1, the START switch is manually moved to the
locked OFF position. At OFF, the pilot valve closes, closing
the start valve and deenergizing the STARTER ON
indicator light. A relay in each engine start circuit is energized
when either START switch is at MTR or START.
The relay, when energized, disables the start circuit of
the opposite engine, thus preventing simultaneous dual
engine starts. Power is supplied by the No. 1 and No. 2
DC essential buses through the ENGINE NO. 1 and NO.
2 START & TEMP AND IGN CIRCUIT BREAKERS ON
THE No. 1 AND No. 2 PDP.
TM 1-1520-240-10
2-3-5
Figure 2-3-4. ENGINE START PANEL 712
2-3-15. START Panel. 712
The START panel is located on the overhead switch panel
(fig. 2-3-4). It consists of the ENG 1 and ENG 2 STARTER
ON indicator lights and two start switches.
a. Start Switches. The switches are labeled OFF,
MTR, and START. They are locked in OFF, detented in
MTR and spring-loaded from START to MTR. At MTR,
the engine is rotated by the starter, but ignition and start
fuel circuits are deenergized. At START, the engine is
rotated with start fuel and the ignition circuits are energized.
MTR is selected during starting, in case of engine
fire or to clear the combustion chamber.
b. STARTER ON Indicator Lights. The STARTER
ON indicator lights will illuminate when the associated
START switch is moved to MTR or START. The light
alerts the pilots when the START switch is inadvertently
left at MTR. Power is supplied by the No. 1 and No. 2 DC
essential buses through the ENGINE NO. 1 and NO. 2
START & TEMP circuit breakers on the No. 1 and No. 2
PDP.
2-3-16. Ignition Lock Switch.
An ignition system lock switch (11, fig. 2-1-3) is installed
on the right side of the console forward of the thrust lever.
The key-operated switch prevents unauthorized use of
the helicopter. When the switch is off, the circuits of the
ignition exciters and the start fuel solenoids of both engines
are open. Therefore, the engines cannot be started.
Be sure both START switches are OFF before turning
the ignition lock switch ON or OFF.
2-3-17. Engine Instruments and Cautions.
The engine instruments are the gas producer tachometer,
the dual torquemeter, power turbine inlet temperature
(PTIT), fuel flow, oil pressure and oil temperature
indicators. The caution capsules are the NO. 1 and NO.
2 ENGINE OIL LOW and the NO. 1 and NO. 2 ENG CHIP
DET.
2-3-18. Gas Producer Tachometer.
Two gas producer tachometers (N1), one for each engine,
are on the center instrument panel (6, fig. 2-1-8 and
6, 2-1-12), above the PTIT indicators. Each tachometer
displays gas producer turbine speed in percent of N1.
Each tachometer operates from power supplied by a gas
producer tachometer generator on the accessory gear
box section of each engine. 712 The outer scale of the
tachometer is calibrated from 0 to 100 in increments of
two. The smaller, vernier scale is calibrated from 0 to 10,
in increments of one. 714A The tachometer is calibrated
from 0 to 110.
2-3-19. Torquemeter.
One torquemeter is on the copilot instrument panel and
the other on the pilot instrument panel (1, fig. 2-1-7 and
17, fig. 2-1-9). Each torquemeter has two pointers, one
for each engine, labeled 1 and 2. Each torquemeter has
a range of 0 to 150 percent. The system consists of a
power output shaft, torquemeter head assembly, power
supply unit, 714A ratio detector power supply unit
　
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