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庞巴迪环球5000公务机机组操作手册 Bombardier Global-动力装置(18)

时间:2011-11-11 09:42来源:蓝天飞行翻译 作者:公务机 点击:
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AUTOTHROTTLE

GF1810_046
A normal disconnect results in a 1 second aural warning as AT1 or AT2 is removed from the PFD. An abnormal disconnect results in flashing AT1 or AT2 annunciation continuously, along with a continuous aural warning, until the crew confirms the disengagement by pressing the quick disconnect button (s).
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
POWER PLANT
 
AUTOTHROTTLE SYSTEM (CONT'D) A/T Engagement/Disengagement (Cont’d) Disengagement (Manual Override)
Manual disengagement of the autothrottle system, for both inflight and on-ground operation, is accomplished by the crew in the following manner:
.  
Pressing the quick disconnect button(s), located on either thrust lever, while the system is engaged or in an on-ground armed state (normal disconnect).

.  
Toggling an engage/disengage switch, located on either thrust lever, while the system is engaged or in an on-ground armed state (normal disconnect).

.  
Overriding the system by manually positioning the thrust levers, while A/T is engaged (abnormal disconnect). Movement of the thrust levers while in an on-ground T/O armed state, will not disconnect the system.


1 Pressing quick disconnect button(s). 2 Toggling an engage/disengage switch.
190  ROLL  TO  3 000 
AUTOTHROTTLE  180 170  A/T1  20  20  1500 
160 
150 6 
145  1000 

3 Overriding by manually advancing or retarding the thrust levers.
NOTE
The thrust levers may retarded during a rejected take-off above 60 knots, without manually disengaging or overpowering the A/T servos. The servos are unpowered above 60 knots when the A/T enters into HOLD THRUST mode. An abnormal disconnect warning will be generated if the disengage switch is not pressed.
GF1810_047
Volume 2  Flight Crew Operating Manual Rev 2A, Apr 11, 2005

POWER PLANT
 
AUTOTHROTTLE SYSTEM (CONT'D)
A/T Mode Operation
The A/T system is integrated with the flight control systems of the airplane to provide compatibility with the active pitch mode of the Flight Guidance System (FGS). The flight guidance pitch mode is normally determined by the flight director or autopilot and is influenced by the FMS during vertical navigation control. The A/T mode operation results in A/T thrust control which complements the pitch control being performed by the FGS. In the event that no FGS pitch mode is active, the A/T will provide independent thrust control based on internally computed mode.
The following table outlines the integrated functional control provided by the A/T and FGS for the various control modes of the AP/FD and FMS for specified phases of a typical flight.
56 7
4

8
3

9

12 13
2
10
1
11
Typical Flight Profile
 
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