* Assuming a constant flow at a pressure altitude of 20,000 feet. Actual time will vary with actual altitude, i.e., less at altitudes above 20,000 feet, more at altitudes below 20,000 feet.
Sec. 17 Page 8
MD-80 Rev. 12/01/00 #29 Continental Flight Manual
Oxygen CYLINDER PRESSURE Gage
Indicates cylinder pressure at all times. Full mark at 1800 +0 -20 psi.
NOTE
FOR LOCATION, REFER TO EMERGENCY EXITS AND EQUIPMENT, THIS CHAPTER.
MD806069
Continuous Flow Outlet
Accommodates continuous flow mask.
(Continuous flow 100% oxygen). Flow - 3
liters per minute. Duration - approximately
100 minutes
(Full cylinder).
SHUTOFF VALVE
LOW PRESSURE RELIEF VALVE
DEMAND REGULATOR
CARRYING
STRAP
CREW OXYGEN CYLINDER (1) 11 CUBIC FEET
PORTABLE OXYGEN CYLINDER – FLIGHT COMPARTMENT PORTABLE OXYGEN CYLINDERS - PASSENGER COMPARTMENT
Sec. 17 Page 10
MD-80 Rev. 12/01/00 #29 Continental Flight Manual
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LIST OF EFFECTIVE PAGES PAGE
DATE PAGE DATE
PAGE DATE
* TOC-1 12/01/00
* TOC-2 12/01/00
* 1 12/01/00
* 2 12/01/00
* 3 12/01/00
* 4 12/01/00
* 5 12/01/00
* 6 12/01/00
* 7 12/01/00
* 8 12/01/00
* 9 12/01/00
* 10 12/01/00
* LEP-1 12/01/00
* LEP-2 12/01/00
* Asterisk indicates page(s) revised or added by the current revision.
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POWER PLANT
TABLE OF CONTENTS
POWER PLANT ................................................................................ 1
General ....................................................................................... 1
Engine Starting............................................................................ 2
Ignition Systems .......................................................................... 3
Engine Oil System....................................................................... 4
Engine Fuel System .................................................................... 4
Thrust Reversers ......................................................................... 5
Engine Synchronizer System....................................................... 6
Thrust Recoveries for Engine Failure During Takeoff................... 6
Thrust Settings for Takeoff .......................................................... 8
Continental
Rev. 12/01/00 #29 Flight Manual
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POWER PLANT
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.
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