05 ENGINES, APU, FUEL SYSTEM 1
05 ENGINES, APU, FUEL SYSTEM
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Topics
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Engines
– Overview
– Indications
– Controls & indicators
– System operation
– Engine oil system
– Engine fuel system
– Engine start system
– Normal operation
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APU
– Overview
– Controls & indicators
– Start and shutdown
– Non-normal operation*
Fuel system
– Overview
– Control & indications
– System schematic
– Normal operations
– Non-normal operation*
Normal start
Crossbleed start
Battery start
Ground air source start
Normal shutdown
– Non-normal operation*
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Engines
Engines
Specifications
Indications
The airplane is powered by two CFM56–7 engines. The engine is a dual–rotor,
axial–flow turbofan. The N1 rotor consists of a fan, a low–pressure compressor
and a low–pressure turbine. The N2 rotor consists of a high–pressure
compressor and a high–pressure turbine. The N1 and N2 rotors are
mechanically independent. The N2 rotor drives the engine gearboxes (IDG,
hydraulic, fuel, oil pumps). A bleed–air–powered starter motor is connected to the
N2 rotor.
• Primary engine indications
• A/T limit
• Thr mode
• TAT
• N1 indications
• TAI
• REV
• EGT
Upper DU
• N2 indications
• Fuel quantity indications
• Fuel quantity
• Fuel used
• Fuel flow
A dual–channel electronic engine control (EEC) regulates each engine. The EEC
monitors autothrottle and flight crew inputs to automatically set engine thrust. 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. The forward thrust levers control forward thrust from idle
to maximum. The reverse thrust levers control thrust from reverse idle to maximum
reverse.
• Secondary engine indications
• Oil pressure
• Oil quantity
• Oil temperature
• Engine vibration
• Hydraulic indications (MFD)
• Hydraulic pressure
• Hydraulic fluid quantity
Lower DU
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ELECTRICAL SYSTEM
Engines
Engines
Indications: Crew alerts (Upper DU)
Controls & indicators: Engine start switches
Start valve open
Illuminated (amber) –
• steady – respective engine start valve
open and air is supplied to starter
• blinking – uncommanded opening of
start valve. Alert is displayed and
solid amber boxes are displayed in
unannunciated positions for that
engine. All three boxes blink for ten
seconds, then alert remains on steady
and solid amber boxes are removed.
Low oil pressure
Illuminated (amber) –
• steady – oil press at or below red line
• blinking – with a condition of low oil
pressure. Alert is displayed and
solid amber boxes are displayed in
unannunciated positions for that
engine. All three boxes blink for ten
seconds, then alert remains on steady
and solid amber boxes are removed.
Oil filter bypass
Illuminated (amber) –
• steady – indicates an impending
bypass of scavenge oil filter
• blinking – with an impending bypass.
Alert is displayed and solid amber
boxes are displayed in unannunciated
positions for that engine. All three
boxes blink for ten seconds, then alert
remains on steady and solid amber
boxes are removed
Engine start switches
Ignition select swtich
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05 ENGINES, APU, FUEL SYSTEM
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Engines
Engines
Controls & indicators: Engine display control panel
Control & indicators: Engine panel
N1 set knob
Reverser lights
Spd Ref selector
Engine control lights
Fuel flow switch
Electronic Engine Control
(EEC) switches
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Engines
Engines
Powerplant schematic
Fuel and oil system
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Engines
Engines
Start and ignition system
Trust reverser
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Engines
Engines
Normal operation: Engine start
Normal operation: Battery only start
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ENGINES, APU, FUEL SYSTEM
Engines
Engines
Normal operation: Engine start from ground air source
Normal operation: Crossbleed start
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Engines
Engines
Non-normal operation: Inflight engine start
Non-normal operation:
Aborted engine start
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Engines
Engines
Non-normal operation:
Inflight engine fuel leak
Non-normal operation: Loss of thrust on both engines
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ENGINES, APU, FUEL SYSTEM
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ENGINES, APU, FUEL SYSTEM
Auxiliary Power Unit (APU)
Auxiliary Power Unit (APU)
Overview
Control & indicators: Engine panel
The auxiliary power unit (APU) is a self–contained gas turbine engine installed within a
fireproof compartment located in the tail of the airplane. The APU supplies bleed air for engine
starting or air conditioning. An AC electrical generator on the APU provides an auxiliary AC
power source.
Overspeed light
APU Maintenance light
Fault light
System components
Low oil pressure
APU EGT indicator
APU switch
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ENGINES, APU, FUEL SYSTEM
Auxiliary Power Unit (APU)
Auxiliary Power Unit (APU)
Normal operation
Normal operation
Start procedures
Shutdown procedures
• The automatic start sequence begins by moving the APU switch momentarily to START. This
initiates opening of the air inlet door. When the APU inlet door reaches the full open position
the start sequence begins. After the APU reaches the proper speed, ignition and fuel are
provided. When the APU is ready to accept a bleed air or electrical load the APU GEN OFF
BUS light illuminates.
• Operate the APU for one full minute with no bleed air load prior to shutdown. This
cooling period is recommended to extend the service life of the APU. When the APU switch is
moved to OFF, this time delay is met automatically.
Note: When the APU is started using battery power only, there is no indication on the
electrical metering panel that the APU generator has come on line and is ready to be selected.
Both the frequency and voltage readings are zero until the APU generator is placed on line.
• Moving the APU switch to OFF
- trips the APU generator
- closes the APU bleed air valve
- extinguishes the APU GEN OFF BUS light.
• If the APU does not reach the proper speed with the proper acceleration rate within the time
limit of the starter, the start cycle automatically terminates. The start cycle may take as long as
120 seconds. Automatic shutdown occurs in the event of EGT exceedance.
• Shutdown occurs automatically after 60 seconds. When the APU speed decreases
sufficiently during shutdown, the fuel valve and inlet door close. If the fuel valve does not
close, the FAULT light will illuminate after approximately 30 seconds.
• If the start fails or the APU GEN OFF BUS light fails to illuminate by the end of the start
cycle, a system failure has occurred and the FAULT light illuminates.
• An immediate shutdown can be accomplished by pulling the APU fire switch.
• Operate the APU for one full minute before using it as a bleed air source. This one
minute stabilization is recommended to extend the service life of the APU.
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Fuel system
Fuel system
Overview
Control & indicators: Fuel control panel
The fuel system supplies fuel to the engines and the APU. Fuel is contained in three tanks
located within the wings and wing center section
Eng/Spar valve closed
Fuel temperature indicator
TANK
NO. 1
NO. 2
CENTER
TOTAL
LITERS
4,876
4,876
16,273
26,025
KILOGRAMS*
3,915
3,915
13,066
20,896
Crossfeed valve open light
Filter bypass lights
Crossfeed selector
Center tank fuel pump
Low Pressure lights
* Usable fuel at level attitude, fuel density 0.8029 kg/liter
Fuel pump switches
Main tank fuel pump
Low Pressure lights
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Fuel system
Fuel system
Control & indications: Fuel alert indications
System schematic
ENGINES, APU, FUEL SYSTEM
Fuel LOW Indication
Illuminated (amber) – fuel quantity less than 907
kgs in related main tank:
• fuel quantity arc and digits on tank(s) with low
fuel quantity turn amber
• displayed until quantity is increased to 1134 kgs.
Fuel Configuration (CONFIG) Indication
Illuminated (amber) – center tank quantity greater than 726 kgs,
both center tank pumps are producing low or no pressure and
either engine is running:
• fuel quantity arc and digits on center tank turn amber
• when illuminated, the indications will remain amber until center
tank quantity is less than 363 kgs, one center tank pump is
producing high pressure or both engines are not running.
Fuel Imbalance (IMBAL) Indication
Illuminated (amber) – main tanks differ by more than 453 kgs:
• displayed below main tank with lower fuel quantity
• fuel quantity arc and digits on tank with lower fuel turn amber
• inhibited when airplane is on ground
• inhibited by fuel LOW indication when both indications exist
• displayed until imbalance is reduced to 91 kgs.
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Fuel system
Normal operation:
Fuel balancing
Köszönöm a figyelmet!
Copyright 2005 © Malev Virtual Training Division. All rights reserved.
Elérhetõségek:
Internet: http://www.b737.virtualairlines.hu
E-mail: [email protected]
Elõadó: Hegedüs Zoltán
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