曝光台 注意防骗
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The EECs also control thrust limits during reverser operation.
ACCESSORY DRIVES
GEARS
MAIN BEARINGS
AIR/OIL
HEAT EXCHANGER
FUEL/OIL
HEAT EXCHANGER
AIR
FUEL
OIL
FILTER
OIL
PUMP
OIL
SCAVENGE
PUMP
B
DUAL
787 Flight Crew Operations Manual
Engines, APU -
Engine System Description
7.20.12 Boeing Proprietary
When the reverse thrust levers are pulled aft to the interlock position:
• the autothrottle disengages
• the auto speedbrakes deploy.
When the reverser system is activated:
• the reverser translating sleeves hydraulically move aft
• the fan flow blocker doors rotate into place to direct fan air through
stationary cascade guide vanes
When the interlock releases:
• the reverse thrust levers can be raised to the maximum reverse thrust
position
• the REV indication changes to green when the reverser is fully deployed.
Pushing the reverse thrust levers to the full down position retracts the reversers to
the stowed and locked position. The thrust levers cannot be moved forward until
the reverse thrust levers are fully down.
The EICAS advisory message ENG REV LIMITED (L or R) is displayed if the
reverser cannot deploy when commanded, or can deploy only with reverse thrust
limited to idle. Not all conditions limiting or preventing reverse thrust can be
detected before reverse thrust selection. For these conditions, the reverse thrust
levers cannot be moved beyond the interlock position.
The EICAS advisory message ENG REVERSER (L or R) is displayed on the
ground to indicate a reverser system fault.
787 Flight Crew Operations Manual
Engines, APU -
Engine System Description
Boeing Proprietary 7.20.13
Thrust Reverser Schematic
REV
REV
FIXED CASCADE VANES
DRAG LINK
STOWED
UNLOCKED
(AMBER)
(GREEN)
REVERSE
AIRFLOW TRANSLATING
SLEEVE
BLOCKER DOOR
787 Flight Crew Operations Manual
Engines, APU -
Engine System Description
7.20.14 Boeing Proprietary
Airborne Vibration Monitoring System
The airborne vibration monitoring system monitors engine vibration levels. The
vibration indications are displayed on the secondary engine display. The vibration
source indication is also displayed. If the vibration monitoring system cannot
determine the source (N1, N2 or N3), broadband (BB) is displayed for the affected
engine. Broadband vibration is the average vibration detected.
The airborne vibration monitoring system is primarily intended for engine
condition monitoring, but it is also a useful tool for isolating and determining
corrective action for engine anomalies. There is no certified vibration limit, but
when a high vibration level is reached, the secondary engine parameters are
automatically displayed. Since there are no operating limitations for the airborne
vibration monitoring system, there are no specific flight crew actions (or
procedures) based solely on vibration indication. High N1 vibration indication
would most likely be accompanied by tactile vibration. This is not the case with
high N2 or N3 vibration indication. Both N1, N2, and N3 high vibrations may be
accompanied by anomalies in other engine parameters and will usually respond to
thrust lever adjustment.
Certain engine malfunctions can result in airframe vibrations from the
windmilling engine. As the airplane transitions from cruise to landing, there can
be multiple, narrow regions of altitudes and airspeeds where the vibration level
can become severe. In general, airframe vibrations can best be reduced by
descending and reducing airspeed. However, if after descending and reducing
airspeed, the existing vibration level is unacceptable, and if it is impractical to
further reduce airspeed, the vibration level may be reduced to a previous, lower
level by a slight increase in airspeed.
Engine Failure Alert System
The engine failure alert system provides alerts when actual engine performance is
less than commanded engine performance during a part of the takeoff and for other
phases of flight.
ENG FAIL is displayed on both PFDs (red) and both HUDs if actual thrust is less
than commanded thrust during takeoff with airspeed between 65 knots and (TBD)
knots prior to V1. The PFD and HUD displays are accompanied by the voice
annunciation “Engine Fail,” and the Master WARNING lights illuminating.
The EICAS caution message ENG FAIL (L or R) is displayed if an engine
unexpectedly decelerates to less than idle speed. The message remains displayed
until the engine recovers or the fuel control switch is moved to CUTOFF.
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787机组操作手册Flight Crew Operations Manual 2(56)
