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Page 9
May 30/02
Revision 7
Thrust Reverser Components
Figure 2
OPERATING MANUAL
2A-78-00 PRODUCTION AIRCRAFT SYSTEMS
Page 10
May 30/02
Revision 7
Thrust Reverser Selector Control Valve
Figure 3
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-78-00
Page 11
May 30/02
Revision 7
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
2A-78-00 PRODUCTION AIRCRAFT SYSTEMS
Page 12
May 30/02
Thrust Reverser Simplified
Schematic (Airplanes SN
1000 - 1143 Excluding SN
1034 Not Having ASC 166
/ 166A)
Figure 4
OPERATING MANUAL
2A-78-00
Page 13 / 14
May 30/02
Thrust Reverser Simplified
Schematic (Airplanes
Having ASC 18, Airplanes
SN 1000 - 1143 Excluding
SN 1034 Having ASC 166
/ 166A and Airplanes SN
1034, 1144 and
Subsequent)
Figure 5
OPERATING MANUAL
2A-78-00
Page 15 / 16
May 30/02
ENGINE OIL
2A-79-10: Engine Oil System
1. General:
A. Description:
The oil system is a self-contained, full flow re-circulatory type that gives
lubricating and cooling oil flow to the engine bearings, gears and splines
throughout the starting, stopping and operational sequence.
B. Operation:
Oil is drawn from the oil tank by a pressure pump. The pump feeds the
engine via an oil cooler and a pressure oil filter, each of which contain a
bypass valve. A relief valve incorporated in the pressure filter ensures that
oil pressure does not exceed a pre-determined value. An oil filter
differential pressure indicator assembly (mounted at the rear of the oil tank)
indicates a blockage in the oil filter.
Oil is returned to the tank by five scavenge pumps and discharged on to a
de-aerator tray. The oil tank vents into the high-speed gearbox which
exhausts through a centrifugal breather.
Feed oil filtration is given by a pressure oil filter, thread and gauze filters.
Return oil filtration is given by gauze strainers and scavenge filters.
C. Subsystems, Units and Components:
• Engine Oil Tank
• Oil Pressure Transmitter
• Low Oil Pressure Switch
• Oil Pump Assembly
• Oil Filter Assembly
• Fuel Cooled Oil Cooler (FCOC)
• Engine Oil Remote Replenishing System
2. Description of Subsystems, Units and Components:
A. Engine Oil Tank:
(See Figure 2.)
The oil supply for engine lubrication is in an oil tank mounted below the oil
cooler on the accessory suspension bracket.
The capacity of each engine oil tank is as follows:
• Left Engine: 6.87 Liters
• Right Engine: 7.3 Liters
A calibrated sight glass, installed on the left-hand wall, shows the amount
of oil necessary to fill the tank to its correct level. The FULL mark shows the
oil capacity of the tank. The sight glass has two graduated scales, one for
the left-hand engine (colored red) and one for the right-hand engine
(colored green).
The oil supply to the pressure pump is drawn from the tank by suction
induced through the rotation of the pump gears. The oil flows from the
bottom of the tank through the supply tube connector on the right-hand wall
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-79-00
Page 1
May 31/01
Revision 4
of the tank. The strainer in the supply connector prevents any foreign
matter contamination in the oil system.
Return oil from the engine main bearings and internal gearbox scavenge
pumps goes into the tank by way of a common tube from the oil pump.
Return oil from the high-speed gearbox scavenge pump goes into the tank
by a separate tube. Both of these tubes discharge the scavenge oil, as an
oil/air mixture, onto the de-aerator tray. The oil flows along the tray which
allows the entrapped air to vent through a tube into the high-speed
gearbox.
B. Oil Pressure Transmitter:
(See Figure 2.)
The oil filter outlet pressure is sensed by the oil pressure transmitter. The
oil pressure transmitter converts oil pressure into an electrical signal and
sends it to a dual-signal conditioner. From there, signal outputs are routed
to the EICAS through their respective DAU. Power for the signal
conditioner is derived from the Essential No. 1, 26V AC transformer bus via
the L ENG OIL PRESS circuit breaker and the Essential No. 2, 26V AC
transformer bus via the R ENG OIL PRESS circuit breaker.
(1) The engine oil pressure parameters (on ground and during takeoff)
are as follows:
• On Ground = Weight On Wheels (WOW)
• Takeoff = Up To Four Minute Period Following WOW
Transition
　
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