The MD-82 doesn't have FADECs - it uses mech linkages to fuel control valves and other assorted bits.
General
The airplane is equipped with two axial-flow, bypass, turbofan Pratt and
Whitney engines. The JT8D-217, -217A and –217C (-219 operated as -
217A) engines have a normal static takeoff thrust rating of 20,000 pounds
and a maximum takeoff thrust rating of 20,850 pounds.
An automatic reserve thrust (ART) system is installed. In the event of an
engine failure, the ART system, when operating, increases the thrust on the
remaining engine.
Each engine is equipped with an acoustic treatment in specific areas for noise
suppression. The engine nacelles are supported from horizontal pylons by
vibration-isolating side mount systems. The nacelles are isolated from the
fuselage by a firewall within the pylon and by a secondary fireseal at the
pylon fuselage interface. To provide additional protection, the secondary
fireseal extends above and below the pylon on the fuselage surface. To
achieve necessary nacelle compartmentation, a fireseal is installed aft of the
rear engine mount, which provides separation of the accessory compartment
from the reverser section. The nacelle ventilation system is designed to
provide adequate cooling of engine and accessories and to prevent
accumulation of combustible mixtures.
For monitoring engine operation, an EPR (engine pressure ratio) gauge,
thrust rating indicator, N1 and N2 tachometers, EGT (exhaust gas
temperature) gauge, FUEL FLOW gauge with a FUEL USED readout, oil pressure
gauge, oil temperature gauge, and fuel temperature gauge are provided for
each engine.
The left and right engine EPR gauges receive sensing signals from the
respective engine air inlet pressure (Pt2) probe and the low pressure turbine
discharge pressure (Pt7) probes. Engine pressure ratio (Pt7/Pt2) is a measure
of thrust being developed by the engine that is displayed on the EPR gauge.
Power to operate these gauges is provided by the respective AC bus.
The thrust rating indicator is interfaced with the ram air temperature probe
and digital flight guidance computer (DFGC) 1 and 2. Ram air temperature
(RAT) and EPR LIM (limit) are displayed on the indicator. Mode buttons are
provided on the indicator for selection of desired mode (T.O., T.O.FLX, GA, MCT,
CL, and CR). The DFGC’s supply data to the indicator for automatic display
of EPR LIM for mode selected.
The left and right N1 tachometers indicate the respective engine low-pressure
compressor rotor RPM as a percentage. The left and right N2 tachometers
indicate the respective engine high-pressure compressor rotor RPM as a
percentage. Power to operate these gauges is self-generated.
The left and right EGT gauges indicate in degrees centigrade the temperature
of the exhaust gas of the respective engine. Each gauge receives signals from
temperature probes located in the exhaust gas path of each engine. Power to
operate these gauges is provided by the Emergency DC bus.
The left and right FUEL FLOW gauges indicate the rate of flow in pounds per
hour that fuel is being delivered to the respective engine. A FUEL USED
readout on each gauge displays a digital readout of fuel used in pounds by the
respective engine. A FUEL USED RESET switch is provided to reset the FUEL
USED readout on both gauges to 00000. For further description of FUEL FLOW
gauge/FUEL USED readout and FUEL USED RESET switch, refer to Fuel section.
Power to operate these gauges is provided by the respective AC bus.
HTH.
ECAM Actions.