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庞巴迪环球5000公务机机组操作手册 Bombardier Global-飞行操纵(2)

时间:2011-11-10 10:26来源:蓝天飞行翻译 作者:公务机
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Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005

TABLE OF CONTENTS 
Page 
DESCRIPTION 
Spoiler System Operation  10.10.46 
Ground Lift Dumping  10.10.46 
Arming  10.10.46 
Deployment  10.10.46 
Disarm  10.10.47 
Spoiler System/FCU Interface  10.10.47 
Spoiler FCU Input Schematic  10.10.48 
Spoiler Control and Monitoring  10.10.49 
Multi-Functional Spoilers  10.10.49 
Ground Spoilers  10.10.49 
Spoiler EICAS Messages  10.10.50 
Stall Protection  10.10.52 
Stall Protection Components  10.10.52 
Angle-Of-Attack (AOA) Vane  10.10.52 
Mach Transducer (On airplanes 9002 thru 9158)  10.10.53 
Stick Shaker Actuator  10.10.53 
Stall Pusher  10.10.54 
Stall Protection Disconnect Buttons  10.10.55 
Stall Pusher On/Off Switches  10.10.56 
Stall Protection Operation  10.10.56 
Stall Warning Advance  10.10.58 
Stall System Pilot Activated Test (On Ground Only)  10.10.59 
Stall Protection Computer  10.10.59 
Stall Protection Computer Schematic  10.10.60 
Stall Protection EICAS Messages  10.10.61 
EMS CIRCUIT PROTECTION 
CB . Flt Controls System  10.20.1 

Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2

TABLE OF CONTENTS
 

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Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
PRIMARY FLIGHT CONTROLS
The primary flight controls consists of two separate elevators, two separate ailerons and a single rudder. The primary flight surfaces are actuated by Power Control Units (PCUs) that are hydraulically powered and mechanically controlled. Artificial control loading (tactile feedback) is provided at the control wheels and rudder pedals. Surface positioning is shown on the EICAS FLIGHT CONTROL synoptic page and trims are shown on the EICAS PRIMARY display.

Each primary control system consists of cable run circuits connected to quadrants. The quadrants receive input from primary control command (flight compartment) using control rod assemblies. The quadrants accept the cable circuit and transmit input to the hydraulically powered primary control surfaces, using control rods and artificial feel assemblies.
Automatic pitch and roll disconnects are provided to allow control of one side of the pitch or roll circuit, in the event of a jam. The roll disconnect mechanism allows the flight crew to isolate the left and right control wheel and cable system from each other. Roll disconnect separates the control wheel interconnect (torque tube) system. Single side roll control is then available (either left or right aileron) using the operable wheel path, with full spoiler control.
 
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