MD-80 Flight Manual 麦道80飞行手册 2(109)

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Auxiliary Power Unit (APU)
The gas turbine-powered APU supplies pneumatic and electrical power for ground operation and electrical power while in flight. The APU is located in the aft accessory compartment and is surrounded by a fireproof enclosure. The unit is protected by a fire detection and a fire extinguishing system which can be operated either from the flight compartment or the external ground control panel located in the left aft fuselage.
Communications
The airplane is equipped with air-to-ground and air-to-air voice flight communication systems. Cockpit / cabin / ground service interphone, passenger address, and voice recorder systems are provided.
Flight attendant, pilot,  mechanic, and passenger call systems are installed in the airplane. This system includes call lights and chime tones.
A separate passenger entertainment system is also provided.
All voice communication is provided through VHF radios.
ACARS is installed to provide automatic data communications for many functions.
Electrical
The airplane is equipped with an AC and DC electrical power system. The systems are divided into two independent systems designated left and right. Two engine-driven AC generators, one on each engine, are normally the primary source of AC power. In the event that engine-driven AC generators fail in flight, or when external power is not available on the ground, auxiliary electrical power may be supplied by an auxiliary power unit driven generator installed in the tail section. The 28-volt DC electrical power is normally supplied by four transformer rectifiers installed in the forward accessory compartment. These T/R’s are supplied 115/120-volt AC power from the AC distribution system. Battery power is supplied by two 14-volt, nickel-cadmium batteries connected in series.
Engines
The airplane is powered by two Pratt and Whitney JT8D axial-flow turbofan engines. In addition to powering the airplane, the engines supply pneumatic power for pressurization, air conditioning, anti-icing, portable water pressure, and de-icing.

Continental
Rev. 12/01/00 #29 Flight Manual
Fire Warning and Protection
The fire warning and protection system provides for continuous detection of engine and/or APU fire, and crewmember notification through visual, aural, and vocal warnings. The airplane is equipped with fire extinguishing capability for each engine nacelle area or for the auxiliary power unit compartment.
Cargo Compartment smoke detection and fire extinguishing is provided by a separate system.
Flight Controls
Primary flight controls consist of conventional aileron, rudder, and elevator control surfaces. Secondary flight controls consist of lift augmenting leading-edge slats, spoilers (lateral control / speedbrake and ground spoilers), inboard and outboard flaps, and horizontal stabilizer. The primary flight controls are cable connected to the control surfaces and are aerodynamically actuated via control tabs. When the secondary flight controls are hydraulically actuated, both the left and right hydraulic systems supply operating power. During powered rudder operation, rudder hydraulic power is supplied by the right hydraulic system. When elevator boost is required, hydraulic power is supplied by the left hydraulic system.
Fuel
The fuel system consists of three integral tanks - one in each wing and one in the wing center section. The tanks are normally filled through a single-point, pressure-fueling adapter, located approximately mid-span of the right wing leading edge. The pressure-fueling control panel is located just inboard of this adapter. A manual defueling valve is located just inboard of the pressure-fueling control panel to permit defueling or fuel transfer through the pressure-fueling adapter.
An overwing gravity fueling adapter is located on top of the outboard section of each wing tank.
Some airplanes are also equipped with two auxiliary fuselage fuel tanks; one in the mid cargo compartment and one in the aft cargo compartment. These tanks are not used at CAL.
Hydraulics
Hydraulic power is provided by two separate, hydraulically closed-circuit systems identified as the left system and the right system. The right system provides hydraulic power to the rudder, aft passenger entrance stairway, and the landing gear actuating subsystem; the left system provides hydraulic power to the elevator augmentor.  All other hydraulic subsystems are served by both systems through separate valves and actuators. The primary source of hydraulic power for each system is an engine-driven pump with an electrically powered auxiliary pump in the right system. There is a power transfer unit between the right and left systems with adequate capacity to transfer full available power between systems.
Ice and Rain Protection
Ice and rain protection is provided for various areas and components of the airplane by the following systems:
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