OPERATIONS MANUAL

Power Plant
System Overview:
The aircraft is fitted with four engines—sometimes referred to as
power plants. Each engine can provide forward and reverse thrust,
and includes components that generate bleed air, electrical power, and
hydraulic power to drive various systems onboard the aircraft (refer to
chapters Air Systems, Electrical, and Hydraulics). The engine thrust
is controllable manually and automatically (refer to chapter Automatic
Flight); and the electronic engine control (EEC) maintains rotor speeds
and other parameters within the allowable limits.—Some aircraft are
equipped with engine autostart systems.
Either General Electric (GE), Pratt & Whitney (PW), or Rolls-Royce (RR)
engines are installed on the aircraft. The exact model depends on the
aircraft variant:
For extended-range (ER) aircraft, the engine models available are:
• CF6-80C2B5F (GE)
• PW4062 (PW)
• RB211-524H8 (RR)
For non-ER aircraft:
• CF6-80C2B1F (GE)
• PW4056 (PW)
• RB211-524G (RR)
The major differences between the engine models being:
• Engine strut size: affects maximum available wing tank fuel volume
• Fire and overheat protection (refer to chapter Fire Protection)
• Thrust reverser mechanism: hydraulically or pneumatically driven
• Turbine design: two-rotor or three-rotor system
• Thrust measuring method: integrated EPR, core EPR, no EPR
• Specific operation limits re EGT, oil, N1, N2, and other parameters
• Electronic engine control specification
• Ignition system logic
• Engine bleed air system design
• Hydraulic EDP pressure minimum for automatic demand pump start
• EICAS symbology
SYSTEM
ANALYSIS
In the simulator, the status of bleed air valves (PRSOVs), start valves, fuel
shutoff valves (SOVs), fuel valves, ignition exciters, and fuel control switch
run time (seconds) are indicated on Instructor > Analysis > Miscellaneous.
O=open; R=Reversed; c=closed; 1=igniter 1; 2=igniter 2; B=both igniters.
The data strings are also accessible through the simulator’s main network.
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