MD-11 Flight Crew Operations Manual
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Engines Chapter Eng
Description and Operation Section 10
Eng.10.1
Eng.10 Engines-Description and Operation
General
The aircraft is equipped with three GE CF6-80C2 engines.
Each engine has dual rotors, a Low Pressure Compressor (LPC) (N1)
incorporating a high bypass ratio turbofan, and a High Pressure Compressor
(HPC) (N2).
A multiple stage (low and high pressure) turbine drives the compressors and fan.
The fan exhaust cowl contains a fan thrust reverser.
The accessory drive section extracts energy from the core engine rotor to drive
accessories and sends core engine speed signals to the Full Authority Digital
Electronic Control (FADEC) system. The accessory gearbox is installed in the
core engine compartment. Mounted on the gearbox are:
•Starter.
• Electrical N2 sensor.
• Fuel pump.
• Lube and scavenge pump.
• Integrated Drive Generator (IDG).
• Hydraulic pumps.
• Alternator (powers the FADEC computer).
Engine controls are on the forward and aft overhead panel and forward pedestal.
Primary engine indications are shown on the upper 2/3 of the Engine and Alert
Display (EAD). The lower 1/3 of the EAD is used for alert presentation.
Secondary engine indications are shown on the System Display (SD) secondary
engine page. The secondary engine page is a default page and is presented
automatically if any parameter on this page exceeds limits.
Full Authority Digital Electronic Control (FADEC)
FADEC is an engine control system that includes the following functions:
• Engine acceleration to idle speed during start.
• Acceleration and deceleration limiting.
• Automatic control of available thrust.
• Minimum/approach idle speeds during descents.
• Compressor airflow control.
• Selection of alternate modes from cockpit.
October 02, 2006
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