Type and number of engines, and thrust capacity of each:
Two wing-hung Pratt & Whitney 2037 twin spool axial flow turbofan powerplants.
37,500 lbs thrust each
Does the Boeing 757-200 have an electronic thrust management system?
Yes, engine thrust is set based on operating conditions
May be programmed for different modes, such as reduced thrust, for engine longevity.
What is the primary thrust indication?
Engine Pressure Ratio (EPR)
Definition of EPR:
The ratio of internal engine pressure to ambient/atmospheric pressure.
The greater the ratio, the greater the thrust.
Number of fuel tanks, capacity and location of each:
Right and left wing tanks 15,450 lbs each
Center tank 48,997 lbs
How is fuel pumped from tanks to engines and APU?
Each tank contains two AC motor driven fuel pumps.
Each pump has capacity to supply fuel from its respective tank.
Center, main tank AC pumps operate at twice the output, so that it is used at a greater rate than wing tanks (for structural/stability purposes).
Center tank fuel is used first then each wing tank supplies its respective engine.
No cross-feed transfer, however any tank may be selected to supply any engine.
Left tank contains a DC powered fuel pump as a backup pump.
Why must takeoff EPR be adjusted if air conditioning system is off and/or wing ant icing is on?
Thrust is dependent on the ratio of internal engine pressure to ambient/atmospheric pressure, and systems utilize bleed air pressure from turbine compressor, and will alter that internal pressure. EPR data is based on air conditioning system on and wing anti icing off, so any condition different must be reflected in the final EPR setting.
What is the minimum runway length required at maximum structural takeoff weight?
Approximately 6,000 feet at sea level and under dry conditions (per runway limited takeoff weight tables, and dependent on flap setting).
Longer for higher airport pressure altitudes and wet conditions.
What is the APU and it’s purpose?
Auxiliary power unit.
Turbine powerplant located in the tail cone
Can provide air for air conditioning cabin cooling on ground and source of electrical power on ground or backup to normal sources, in flight
Bleed air for engine starts up to 20,000 feet.
How many independent hydraulic systems are installed?
Three, known as left, right, and center.
Which system is the source for thrust reverser hydraulic power?
Left system for the left engine reverser Right system for the right engine reverser
How is hydraulic power supplied for landing gear operation?
Primarily via the left system, however, may be supplied via right system power transfer unit.
Purpose of flaps and leading-edge slats:
To increase lift by altering the camber of wings Beneficial for takeoff and approach and landing at lower speeds. Leading edge slats only used for landing due to drag produced, counterproductive during takeoff.
Sources of hydraulic power for the elevator, ailerons, and rudder:
All three systems
Ram air turbine hydraulic pump (RAT), when engine N2 RPM is below 50%.
Describe cabin climate control and pressurization:
Two independent engine-driven air conditioning packs pressurize the cabin and is controlled by the amount of air an outflow valve permits.
Cooling on the ground is due to adiabatic expansion of air from the packs.
Warming in flight uses heat from operating engines mixed with ambient air
What is EICAS?
Engine Indication and Crew Alerting System Display of engine and system status, and advisory, caution, or warning alerts on CRT screens.
How is electrical power generated?
Two engine driven generators (AC)
APU generator (AC)
One hydraulic motor driven generator (AC and DC for backup to engine and APU AC)
Main battery for APU start on ground and interior courtesy lights only. (DC)
Which surfaces/components are electrically heated?
Six flight deck windows
Pitot tubes (PIC and SIC and left and right auxiliary) Angle of attack (AOA) vanes Total Air Temperature (TAT) probe
Which surfaces/components are protected by engine bleed air anti icing system?
Leading edges of wings
Engine cowling
Some slats
Describe normal and alternate landing gear braking system:
Multiple discs on each wheel, powered by right hydraulic system.
Left system independently powers alternate braking system when right system pressure is low.
A reserve system is available if both left and right systems fail and is powered via the right system electrical pump.
Accumulator brake system provides emergency pressure for several brake applications when no pressure is available from any other source.
Describe navigation equipment:
Inertial Reference System (IRS)
Flight Management Computer (FMC) aka Flight Management System (FMS)
GPS, VOR, DME, Localizer, Glideslope, and ADF/NDB receivers
Describe external communication equipment:
Three VHF transceivers
Two HF transceivers
Aircraft Communications Addressing and Reporting System (ACARS) SELCAL (incoming notification only)
Describe the fire/overheat detection and fire extinguishing system:
Engines: overheat protection dual fire loops, two fire bottles, manually activated to either engine.
APU: fire detection and one fire bottle manually activated Cargo compartments: smoke detection and two fire bottles total, manually activated Main wheel wells: fire detection only Pneumatic ducts in body and wings: overheat detection only
How many doors are available for evacuation?
Eight (L1-4 and R1-4)
