曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

When the switch is set to RED, the red lights come on.
OFF position turns off both sets of lights.
c. ALARM switch. The two-position ALARM switch
is labeled OFF and ON. Moving the ALARM switch to ON
rings the bell continuously at both stations until the switch
is moved to OFF.
Figure 2-2-2. Troop Warning Panel (Typical)
2-2-9. First Aid Kits.
Seven aeronautic first aid kits are installed in the helicopter.
One kit is in the passageway between the cockpit and
cabin. The other six kits are in the cabin fuselage section,
three on each side.
2-2-10. Emergency Entrances and Exits.
Refer to Chapter 9 for information on emergency entrances
and exits.
2-2-11. Emergency Escape Axe.
An emergency escape axe is provided. It is located on
the right side of the cargo compartment slightly forward
of station 200.
TM 1-1520-240-10
2-3-1
SECTION III. ENGINES AND RELATED SYSTEMS
2-3-1. Engines.
The CH-47D is powered by either two T55-L-712 or two
T55-GA-714A engines. The engines are housed in separate
nacelles mounted externally on each side of the aft
pylon. The engines have the capability to produce emergency
power on pilot demand. See Performance Charts
in Chapter 7 712 or Chapter 7A 714A .
2-3-2. General
Each engine has a gas producer section and a power
turbine section. The gas producer supplies hot gases to
drive the power turbine. It also mechanically drives the
engine accessory gearbox. The power turbine shaft extends
coaxially through the gas producer rotor and rotates
independently of it. The gas producer section and
the power turbine section are connected by only the hot
gases which pass from one section to the other.
During engine starting, air enters the engine inlet and is
compressed as it passes through seven axial stages and
one centrifugal stage of the compressor rotor. The compressed
air passes through a diffuser. Some of the air
enters the combustion chamber where it is mixed with
start fuel.
The mixture ignited by four igniter plugs. Some of the air
is directed to the fuel nozzles. After the engine is started,
it continues to operate on metered fuel supplied to the
fuel nozzles.
Hot expanding gases leave the combustion chamber and
drive a two-stage gas producer turbine. Energy from the
combustion gases also drives the two-stage power turbine,
which drives the power turbine shaft to the engine
transmission. The engine lubrication system has an integral
oil tank which is inside the air inlet housing and is
serviced with approximately 12 quarts. (Refer to table
2-15-1.)
2-3-3. Engine Inlet Screens.
An engine inlet screen which minimizes foreign object
damage (FOD) is installed on each engine. The reduction
in engine power available with screens installed is
negligible. The engine inlet screens have bypass panels.
These two panels are on the aft end of each screen.
Refer to Chapter 5 for information on use of bypass panels.
Helicopters with engine air particle separator (EAPS)
installed, refer to TM 1-1520-240-10 EAPS SUPPLEMENT.
2-3-4. Engine Anti–Icing.
The engine air inlet fairing and engine drive shaft fairing
receive anti-icing protection from the thermal radiation
produced by the oil tank in the engine inlet housing. The
hot oil in the oil cavity of the inlet housing warms the air
as it passes into the engine inlet.
2-3-5. Engine Power Control System. 712
Each engine is controlled by a separate power control
system which includes cockpit controls and an engine
fuel control unit. Each system provides automatic control
of engine gas producer rotor speed and power turbine
speed in response to any setting of the engine controls
selected by the pilot. Engine gas producer rotor speed
(N1) and power turbine speed (N2) are controlled by the
fuel control unit, which varies the amount of fuel delivered
to the engine fuel nozzles. During normal operation, the
fuel control unit automatically controls fuel flow metering
during power changes, thus protecting the engine from
overspeed and overtemp. Fuel flow is automatically
monitored to compensate for changes in outside air temperature
and compressor discharge pressure.
2-3-6. Engine Fuel Control Units. 712
Each engine fuel control unit contains a single element
fuel pump, a gas producer speed governor, a power turbine
speed governor, an acceleration-deceleration control,
a fuel flow limiter, a fuel control shutoff valve, and a
main metering valve. A gas producer (N1) lever and a
power turbine (N2) lever are mounted on the fuel control
unit.
　
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：支奴干運(yùn)輸直升機(jī)操作手冊(cè)1(14)