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autothrottle does not automatically retard if the pitch mode is TO/GA or FLCH.
The autothrottle can be manually overridden or disconnected by pushing either
autothrottle disconnect switch.
With the autothrottle armed, the autothrottle automatically activates if:
• no autopilot or flight director active, or
• an autopilot or flight director is in VNAV XXX, FPA, ALT, V/S, or G/S
787 Flight Crew Operations Manual
Automatic Flight -
System Description
4.20.10 Boeing Proprietary
and:
• speed less than an FMC calculated value for one second
• thrust below reference thrust
• airplane altitude above 100 feet RA on approach, or airplane barometric
altitude 400 feet above airport on takeoff.
The EICAS advisory message AUTOTHROTTLE L or R is displayed when the
respective autothrottle servo fails. If the autothrottle is activated and only one
autothrottle is armed, the PFD autothrottle flight mode annunciation displays L or
R preceding the mode. For example, L SPD indicates only the left autothrottle is
activated in the speed mode.
Autothrottle Thrust Lever Operation
The autothrottle system moves either or both thrust levers to provide speed or
thrust control, depending on the mode activated.
The thrust levers can be manually positioned without disconnecting the
autothrottle. After manual positioning, the autothrottle system repositions the
thrust levers to comply with the activated mode. The autothrottle system does not
reposition the thrust levers while in HOLD mode.
Autothrottle Disconnect
The autothrottle system can be disconnected manually by pushing either thrust
lever autothrottle disconnect switch, except during conditions that cause the
autothrottle to automatically activate. The autothrottle can also be disconnected
manually by positioning both A/T ARM switches to OFF, or individually by
positioning the left or right A/T ARM switch to OFF. Positioning one or both A/T
ARM switches to OFF prevents activation of all autothrottle modes for the
affected autothrottle.
Autothrottle disconnect occurs automatically:
• if a fault in the active autothrottle mode is detected
• when either reverse thrust lever is raised to reverse idle
• if the thrust levers are overridden during a manual landing, after the
autothrottle has begun to retard the thrust levers to idle
• when both engines are shut down.
The EICAS caution message AUTOTHROTTLE DISC is displayed and an aural
alert sounds when the autothrottle is manually or automatically disconnected. The
EICAS caution message and aural alert are inhibited if the disconnect occurs
because of reverse thrust.
787 Flight Crew Operations Manual
Automatic Flight -
System Description
Boeing Proprietary 4.20.11
Automatic Flight Operations
Automatic Flight Takeoff and Climb
Takeoff is a flight director only function of the takeoff/go–around (TO/GA) mode.
The autopilot may be engaged after takeoff.
During preflight:
• With the autopilot disengaged and both flight director switches OFF,
engagement of TO/GA roll and pitch mode occurs when the first flight
director switch is positioned ON.
• The PFD and HUD displays FLT DIR as the AFDS status and TO/GA as
the pitch and roll flight mode annunciations.
• The pitch command is a fixed attitude (about eight degrees up).
• The roll command is wings level.
During takeoff prior to lift–off:
• With speed less than 50 KIAS, pushing a TO/GA switch activates the
autothrottle in the thrust reference (THR REF) mode. The thrust levers
advance to the selected thrust limit. If the autothrottle is not activated by
50 knots, it cannot be activated until above 400 feet.
• At 80 knots, the autothrottle mode annunciation changes to HOLD.
• With speed greater than 80 knots, pushing a TO/GA switch disarms
LNAV and VNAV.
• During takeoff, the FMC records the barometric altitude as the airplane
accelerates through 100 knots. This altitude is used to engage VNAV,
enable autothrottle activation (if not active), command acceleration for
flap retraction, and set climb thrust if an altitude has been selected. Radio
altitude is used for engagement of LNAV.
At lift–off:
• The pitch command target speed is V2 + 15. If current airspeed remains
above the target speed for 5 seconds, the target airspeed is reset to current
airspeed (limited to a maximum of V2 + 25).
• If an engine failure occurs on the ground, the pitch command target speed
at lift–off is V2 or airspeed at lift–off, whichever is greater.
• The roll command maintains ground track.
　
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本文鏈接地址：787機(jī)組操作手冊Flight Crew Operations Manual 2(6)