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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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