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787 Flight Crew Operations Manual
Engines, APU -
Controls and Indicators
7.10.16 Boeing Proprietary
Fuel Control Switches
RUN –
• opens the spar fuel valve
• arms the engine fuel valve (the EEC opens the valve when required)
• arms the selected ignitor(s) (the EEC turns the ignitors on when required)
CUTOFF –
• closes the fuel valves
• removes ignitor power
• unlocks the engine fire switch.
Engine Control Panel
1 FUEL CONTROL Switch
FUEL CONTROL
RUN
CUTOFF
L R
CONTROL STAND
1
NORM
ALTN
START
R
START
NORM
L
NORM
R
START
L
ENGINE
EEC MODE
NORM
ALTN
OVERHEAD PANEL
1
2
3
787 Flight Crew Operations Manual
Engines, APU -
Controls and Indicators
Boeing Proprietary 7.10.17
NORM –
• selects the normal engine control mode for engine control
• the EEC sets thrust using TPR as the controlling parameter.
Off (ALTN visible) –
• selects the alternate engine control mode for engine control
• thrust is set using N1 RPM as the controlling parameter.
Illuminated (amber) – the alternate engine control mode is either automatically or
manually selected.
START –
• initiates engine start by commanding the engine starter motor to energize
• releases to NORM at completion of start
NORM – the starter is de-energized
Auxiliary Power Unit (APU)
APU Controls
OFF –
• initiates normal shutdown
• resets auto shutdown fault logic.
1 Electronic Engine Control (EEC) Mode Switch
2 Electronic Engine Control (EEC) Alternate (ALTN) Light
3 START Selector
1 APU Selector
APU
ON
OFF
FAULT
START
OVERHEAD PANEL
1
2
787 Flight Crew Operations Manual
Engines, APU -
Controls and Indicators
7.10.18 Boeing Proprietary
ON (APU operating position) –
• opens the APU fuel valve and inlet door
• activates AC or DC fuel pump
• powers the APU controller.
START (momentary position, spring–loaded to ON) – initiates automatic start
sequence.
Illuminated (amber):
• APU fault and/or fire is detected
• APU shutdown due to fault and/or fire
• momentarily during APU controller self–test.
APU Indications
RPM – APU rotation speed in percent RPM.
EGT – APU exhaust gas temperature.
OIL PRESS – APU oil pressure in PSI.
OIL TEMP – APU oil temperature.
OIL QTY – APU oil quantity (quarts).
2 APU FAULT Light
1 APU Status Display
EGT C
PSI OIL TEMP C OIL QTY
RPM
OIL PRESS 7.4
100.1 350
65 75
APU
MFD STATUS DISPLAY
1
787 Flight Crew Operations Manual
Engines, APU Chapter 7
Engine System Description Section 20
Boeing Proprietary 7.20.1
7.20 Engines, APU-Engine System Description Introduction
The airplane is powered by two Rolls Royce Trent 1000 engines. The engines are
rated at 63,800 pounds of takeoff thrust each.
The engines are three-rotor axial flow turbofans of high compression and bypass
ratio. The N1 rotor consists of the fan and a low pressure turbine section on a
common shaft. The N2 rotor consists of an intermediate pressure compressor
section and an intermediate pressure turbine section on a common shaft. The N3
rotor consists of a high pressure compressor section and a high pressure turbine
section on a common shaft. The N1 rotor is mechanically independent from the
N2 and N3 rotors. The N2 and N3 rotors are mechanically independent when the
engine is at or above idle. Below idle, a start power coupling engages, connecting
the N2 and N3 rotors. The N2 rotor drives the engine accessory gearbox.
Each engine is controlled by an electronic engine controller (EEC). The EECs
monitor autothrottle and flight crew inputs through the thrust levers to
automatically control the engines.
Each engine has individual flight deck controls. Thrust is set by positioning the
thrust levers. The thrust levers are positioned automatically by the autothrottle
system or manually by the flight crew. See Chapter 11, Flight Management,
Navigation, Section 32, for a description of FMC thrust management functions.
Engine indications are displayed on the engine indication and crew alerting
system (EICAS) display.
Engine Indications
Primary and secondary engine indications are provided. Engine indications are
only displayed on the EICAS display. Normally EICAS is on the inboard window
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787机组操作手册Flight Crew Operations Manual 2(51)
